Airworthiness Directives; Airbus Model A300 B2 and B4 Series Airplanes

DEPARTMENT OF AGRICULTURE

DEPARTMENT OF TRANSPORTATION

14 CFR Part 39

[Docket No. 95-NM-109-AD]

RIN 2120-AA64

Airworthiness Directives; Airbus Model A300 B2 and B4 Series

Airplanes

AGENCY: Federal Aviation Administration, DOT.

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ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the supersedure of an existing

airworthiness directive (AD), applicable to certain Airbus Model A300

B2 and B4 series airplanes, that currently requires inspection for

cracks of the fuselage, wings, and vertical stabilizer structures; and

repairs or modifications, if necessary. That AD was prompted by reports

of cracking in several areas of the fuselage, wings, and vertical

stabilizer structure due to fatigue-related stress. The actions

specified by that AD are intended to prevent such fatigue-related

cracking, which could result in reduced structural integrity of the

fuselage, wing, and vertical stabilizer. This action would provide for

a new optional terminating action, for certain airplanes, and would

expand the applicability of the existing AD to include additional

airplanes.

DATES: Comments must be received by June 10, 1996.

ADDRESSES: Submit comments in triplicate to the Federal Aviation

Administration (FAA), Transport Airplane Directorate, ANM-103,

Attention: Rules Docket No. 95-NM-109-AD, 1601 Lind Avenue SW., Renton,

Washington 98055-4056. Comments may be inspected at this location

between 9:00 a.m. and 3:00 p.m., Monday through Friday, except Federal

holidays.

The service information referenced in the proposed rule may be

obtained from Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac

Cedex, France. This information may be examined at the FAA, Transport

Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington.

FOR FURTHER INFORMATION CONTACT: Phil Forde, Aerospace Engineer,

Standardization Branch, ANM-113, FAA, Transport Airplane Directorate,

1601 Lind Avenue SW., Renton, Washington 98055-4056; telephone (206)

227-2146; fax (206) 227-1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested persons are invited to participate in the making of the

proposed rule by submitting such written data, views, or arguments as

they may desire. Communications shall identify the Rules Docket number

and be submitted in triplicate to the address specified above. All

communications received on or before the closing date for comments,

specified above, will be considered before taking action on the

proposed rule. The proposals contained in this notice may be changed in

light of the comments received.

Comments are specifically invited on the overall regulatory,

economic, environmental, and energy aspects of the proposed rule. All

comments submitted will be available, both before and after the closing

date for comments, in the Rules Docket for examination by interested

persons. A report summarizing each FAA-public contact concerned with

the substance of this proposal will be filed in the Rules Docket.

Commenters wishing the FAA to acknowledge receipt of their comments

submitted in response to this notice must submit a self-addressed,

stamped postcard on which the following statement is made: ``Comments

to Docket Number 95-NM-109-AD.'' The postcard will be date stamped and

returned to the commenter.

Availability of NPRMs

Any person may obtain a copy of this NPRM by submitting a request

to the FAA, Transport Airplane Directorate, ANM-103, Attention: Rules

Docket No. 95-NM-109-AD, 1601 Lind Avenue SW., Renton, Washington

98055-4056.

Discussion

On August 13, 1986, the FAA issued AD 86-19-02, amendment 39-5396

(51 FR 29910, August 21, 1986), applicable to certain Airbus Model A300

B2 and B4 series airplanes. That AD requires inspections for cracks of

the fuselage, wings, and vertical stabilizer structures; and repairs or

modifications, if necessary. That action was prompted by reports that,

during fatigue tests conducted by the manufacturer, cracks were

detected in several areas of the fuselage, wings, and vertical

stabilizer structure. The requirements of that AD are intended to

prevent reduced structural integrity of the fuselage, wing, and

vertical stabilizer.

Explanation of New Relevant Service Information

Since the issuance of that AD, Airbus has issued Revision 3 of

Service Bulletin A300-53-182, dated March 16, 1994. The inspection

procedures described in this revision are identical to those described

in the original version of the service bulletin, which was referenced

in AD 86-19-02 as the appropriate source of service information.

However, this new revision of the service bulletin differs in two ways

from the original version:

1. The effectivity listing in the revised bulletin includes

additional airplanes that are subject to the addressed unsafe

condition.

2. For certain airplanes, the revised service bulletin provides

procedures for replacement of the web plate and support fitting at the

level of stringer 18 (left- and right-hand) with a new web plate and

support fitting. Accomplishment of the replacement would eliminate the

need for the repetitive inspections in the web plate between frame 30A

and frame 32 at stringer 18.

The Direction Generale de l'Aviation Civile (DGAC), which is the

airworthiness authority for France, classified this service bulletin as

mandatory and issued French airworthiness directive (CN) 83-102-

053(B)R2, dated March 2, 1994, in order to assure the continued

airworthiness of these airplanes in France.

Explanation of the Provisions of the Proposed Rule

This airplane model is manufactured in France and is type

certificated for operation in the United States under the provisions of

section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and

the applicable bilateral airworthiness agreement. Pursuant to this

bilateral airworthiness agreement, the DGAC has kept the FAA informed

of the situation described above. The FAA has examined the findings of

the DGAC, reviewed all available information, and determined that AD

action is necessary for products of this type design that are

certificated for operation in the United States.

Since an unsafe condition has been identified that is likely to

exist or develop on other airplanes of the same type design registered

in the United States, the proposed AD would supersede AD 86-19-02 to

continue to require inspections for cracks of the fuselage, wings, and

vertical stabilizer structures; and repairs or modifications, if

necessary. However, the applicability of the rule would be expanded to

include additional airplanes that have been identified as subject to

the addressed unsafe condition.

For certain airplanes, the proposed AD would provide for a new

optional replacement action, which would constitute terminating action

for certain repetitive inspection requirements. These actions would be

required to be accomplished in accordance with the service bulletin

described previously.

Operators who previously elected to accomplish Airbus Modification

1691 to terminate the repetitive inspections at stringers 18 and 22, as

was provided by paragraph D. of AD 86-19-02, should note that, under

the provisions of paragraph (d)(4) of this proposal, accomplishment of

that modification

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would constitute terminating action for the repetitive inspections only

at stringer 22.

Additionally, operators should note that paragraph G. of AD 86-19-

02 has not been retained in this proposal. That paragraph required

ultrasonic inspections of the longitudinal lap joints at stringer 29

between frames 72 and 73, and eddy current inspections of the

longitudinal skin splices of the top fuselage joint between frames 72

and 80. The FAA has issued a separate rulemaking action to address

those requirements (reference notice of proposed rulemaking, Docket No.

94-NM-246-AD).

Cost Impact

Approximately 7 Airbus Model A300 B2 and B4 series airplanes of

U.S. registry would be affected by this proposed AD.

The actions that are currently required by AD 86-19-02 take

approximately 919 work hours per airplane to accomplish, at an average

labor rate of $60 per work hour. The cost of required parts will be

nominal. Based on these figures, the cost impact on U.S. operators of

the actions currently required is estimated to be $385,980, or $55,140

per airplane, per inspection cycle.

The new actions that are proposed in this AD action would take

approximately 3 work hours per airplane to accomplish, at an average

labor rate of $60 per work hour. Based on these figures, the cost

impact on U.S. operators of the proposed requirements of this AD is

estimated to be $1,260, or $180 per airplane.

The cost impact figures discussed above are based on assumptions

that no operator has yet accomplished any of the current or proposed

requirements of this AD action, and that no operator would accomplish

those actions in the future if this AD were not adopted.

Regulatory Impact

The regulations proposed herein would not have substantial direct

effects on the States, on the relationship between the national

government and the States, or on the distribution of power and

responsibilities among the various levels of government. Therefore, in

accordance with Executive Order 12612, it is determined that this

proposal would not have sufficient federalism implications to warrant

the preparation of a Federalism Assessment.

For the reasons discussed above, I certify that this proposed

regulation (1) is not a ``significant regulatory action'' under

Executive Order 12866; (2) is not a ``significant rule'' under the DOT

Regulatory Policies and Procedures (44 FR 11034, February 26, 1979);

and (3) if promulgated, will not have a significant economic impact,

positive or negative, on a substantial number of small entities under

the criteria of the Regulatory Flexibility Act. A copy of the draft

regulatory evaluation prepared for this action is contained in the

Rules Docket. A copy of it may be obtained by contacting the Rules

Docket at the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

Accordingly, pursuant to the authority delegated to me by the

Administrator, the Federal Aviation Administration proposes to amend

part 39 of the Federal Aviation Regulations (14 CFR part 39) as

follows:

PART 39--AIRWORTHINESS DIRECTIVES

1. The authority citation for part 39 continues to read as follows:

Authority: 49 U.S.C. 106(g) 40113, 44701.

Sec. 39.13 [Amended]

2. Section 39.13 is amended by removing amendment 39-5396 (51 FR

29910, August 21, 1986), and by adding a new airworthiness directive

(AD), to read as follows:

Airbus Industrie: Docket 95-NM-109-AD. Supersedes AD 86-19-02,

Amendment 39-5396.

-Applicability: All Model A300 B2 and B4 series airplanes,

certificated in any category.

Note 1: This AD applies to each airplane identified in the

preceding applicability provision, regardless of whether it has been

otherwise modified, altered, or repaired in the area subject to the

requirements of this AD. For airplanes that have been modified,

altered, or repaired so that the performance of the requirements of

this AD is affected, the owner/operator must request approval for an

alternative method of compliance in accordance with paragraph (j) of

this AD. The request should include an assessment of the effect of

the modification, alteration, or repair on the unsafe condition

addressed by this AD; and, if the unsafe condition has not been

eliminated, the request should include specific proposed actions to

address it.

Note 2: Airbus Model A300-600 series airplanes are not subject

to this AD.

Compliance: Required as indicated, unless accomplished

previously.

To prevent fatigue-related cracking, which could result in

reduced structural integrity of the fuselage, wing, and vertical

stabilizer, accomplish the following:

(a) For airplanes with serial numbers listed in Airbus Service

Bulletin A300-53-127, Revision 4, dated May 10, 1984: Perform a

visual inspection to detect cracks in the upper fuselage skin at

frame 58 between stringer 5 left and stringer 5 right, in accordance

with the Accomplishment Instructions of the service bulletin, and in

accordance with the times specified in this paragraph.

(1) Perform the initial inspection at the later of the times

specified in paragraph (a)(1)(i) or (a)(1)(ii) of this AD.

(i) Prior to the accumulation of 18,000 total landings or 18,000

total flight hours, whichever occurs earlier; or

(ii) Within one year after September 26, 1986 (the effective

date of AD 86-19-02, amendment 39-5396).

(2) If no crack is detected, repeat this inspection thereafter

at intervals not to exceed 3,000 flight hours.

(3) If any crack is detected, prior to further flight, repair it

in accordance with Figure 2, ``Inspection and Repair Alternative

Chart,'' of the service bulletin.

(4) Installation of Airbus Modification 2147 (reference Airbus

Service Bulletin A300-53-110, Revision 10, dated April 7, 1986) or

Airbus Modification 2526/1693 (reference Airbus Service Bulletin

A300-53-128, Revision 5, dated May 10, 1984) constitutes terminating

action for the repetitive inspection requirements of paragraph

(a)(2) of this AD.

(b) For airplanes with serial numbers listed in Airbus Service

Bulletin A300-53-101, Revision 7, dated May 10, 1984: Perform a

radiographic and ultrasonic inspection to detect cracks in the

circumferential fuselage splice plates and stringer couplings, in

accordance with the Accomplishment Instructions of the service

bulletin, and in accordance with the times specified in this

paragraph.

(1) Perform the initial inspections at the applicable time

specified in paragraph (b)(1)(i) or (b)(1)(ii) of this AD:

(i) For airplanes on which the actions specified in Airbus

Service Bulletin A300-53-053, Revision 2, dated July 30, 1981, have

been accomplished previously: Inspect prior to the accumulation of

20,000 landings since accomplishment of those actions, or within one

year after September 26, 1986, whichever occurs later.

(ii) For airplanes on which the actions specified in Airbus

Service Bulletin A300-53-053, Revision 2, dated July 30, 1981, have

not been accomplished: Inspect prior to the accumulation of 18,000

total landings, or within one year after September 26, 1986,

whichever occurs later.

(2) If no crack is detected, repeat the inspections thereafter

at intervals not to exceed 3,000 landings.

(3) If any crack is detected, prior to further flight, repair it

in accordance with Figures 1 and 2 of the service bulletin.

(4) Installation of Airbus Modification 3760 (reference Airbus

Service Bulletin A300-53-170, Revision 1, dated January 25, 1985)

constitutes terminating action for the repetitive inspection

requirements of paragraph (b)(2) of this AD.

(c) For airplanes with serial numbers listed in Airbus Service

Bulletin A300-53-143, Revision 3, dated May 10, 1984: Perform a

visual inspection to detect cracks in frame

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57A between stringers 15 and 16 (left- and right-hand), and the

stringer 5 connection angle at frame 65 (left- and right-hand), in

accordance with the Accomplishment Instructions of the service

bulletin, and in accordance with the times specified in this

paragraph. .

(1) Perform the initial inspection at the later of the times

specified in paragraph (b)(1)(i) or (b)(1)(ii) of this AD:

(i) Prior to the accumulation of 20,000 total landings; or

(ii) Within one year after September 26, 1986.

(2) If no crack is detected, repeat this inspection thereafter

at intervals not to exceed 3,000 landings.

(3) If any crack is detected, prior to further flight, repair it

in accordance with the service bulletin.

(4) Installation of Airbus Modification 2643 (reference Airbus

Service Bulletin A300-53-132, Revision 4, dated May 10, 1984)

constitutes terminating action for the repetitive inspection

requirement of paragraph (c)(2) of this AD.

(d) For airplanes having serial number 002 through 156

inclusive, on which Airbus Modification 2611 has not been installed:

Perform a visual inspection, and liquid penetrant test if

applicable, to detect cracks in the web plate and support fitting

between frames 30A and 32 at stringer 18, and between stringers 22

and 23 (left- and right-hand), in accordance with Airbus Service

Bulletin A300-53-182, Revision 3, dated March 16, 1994, and in

accordance with the times specified in this paragraph.

(1) Perform the initial inspection at the later of the times

specified in paragraph (d)(1)(i) or (d)(1)(ii) of this AD:

(i) Prior to the accumulation of 30,000 total landings; or

(ii) Within 1,500 landings after the effective date of this AD.

(2) If no crack is detected, repeat the inspection at the

applicable intervals specified in paragraph (d)(2)(i) or (d)(2)(ii)

of this AD.

(i) If, at the time of the most recent inspection, the airplane

has accumulated fewer than 36,000 total landings, repeat the

inspection thereafter at intervals not to exceed 3,000 landings.

(ii) If, at the time of the most recent inspection, the airplane

has accumulated 36,000 or more total landings, repeat the inspection

thereafter at intervals not to exceed 2,000 landings.

(3) If any crack is detected in the web plate between frames 30A

and 32 at stringer 18, prior to further flight, replace the web

plate and support fitting at stringer 18 (left- and right-hand) with

a new web plate and support fitting, in accordance with the service

bulletin. Accomplishment of this replacement constitutes terminating

action for the repetitive inspection requirements for stringer 18 as

required by paragraph (d)(2) of this AD.

(4) If any crack is detected in the web plate between frame 30A

and 32 between stringers 22 and 23, prior to further flight, replace

the web plate and support fitting between stringers 22 and 23 (left-

and right-hand) with a new web plate and support fitting, in

accordance with Airbus Service Bulletin A300-53-182, Revision 3,

dated March 16, 1994. Accomplishment of this replacement constitutes

terminating action for the repetitive inspection requirements for

the subject area between stringers 22 and 23 as required by

paragraph (d)(2) of this AD.

(5) Terminating action for the repetitive inspection

requirements of paragraph (d)(2) of this AD is as follows:

(i) Installation of Airbus Modification 1691 (reference Airbus

Service Bulletin A300-53-063) between stringers 22 and 23

constitutes terminating action for the repetitive inspection

requirements of paragraph (d)(2) of this AD for that area only.

(ii) Replacement of the web plates and support fittings at the

level of stringer 18 (left- and right-hand) with a new web plate and

support fitting, in accordance with Airbus Service Bulletin A300-53-

182, Revision 3, dated March 16, 1994, constitutes terminating

action for the repetitive inspection requirements of paragraph

(d)(2) of this AD for that stringer only.

(iii) Accomplishment of the actions specified in both paragraph

(d)(5)(i) and paragraph (d)(5)(ii) of this AD constitute terminating

action for all repetitive inspection requirements required by

paragraph (d)(2) of this AD.

(e) For airplanes with serial numbers listed in Airbus Service

Bulletin A300-53-112, Revision 2, dated July 20, 1981: Perform a

visual inspection to detect cracks of the skin from frame 28 to

frame 31 between stringers 29 and 31 (left- and right-hand), in

accordance with the Accomplishment Instructions of the service

bulletin, and in accordance with the times specified in this

paragraph.

(1) Perform the initial inspection at the later of the times

specified in paragraph (e)(1)(i) or (e)(1)(ii) of this AD: -

(i) Prior to the accumulation of 24,000 total landings; or

(ii) Within one year after September 26, 1986.

(2) If no crack is detected, repeat the inspection at the

applicable intervals specified in paragraph (e)(2)(i) or (e)(2)(ii)

of this AD:

(i) If, at the time of the most recent inspection, the airplane

has accumulated fewer than 36,000 total landings, repeat the

inspection thereafter at intervals not to exceed 6,000 landings.

(ii) If, at the time of the most recent inspection, the airplane

has accumulated 36,000 or more total landings, repeat the inspection

thereafter at intervals not to exceed 3,000 landings.

(3) If any crack is found, prior to further flight, install

Airbus Modification 1358 in accordance with Airbus Service Bulletin

A300-53-027, Revision 4, dated January 4, 1984. Accomplishment of

this modification constitutes terminating action for the repetitive

inspection requirements of paragraph (e)(2) of this AD.

(4) Installation of Airbus Modification 1358 (reference Airbus

Service Bulletin A300-53-027, Revision 4, dated January 4, 1984)

constitutes terminating action for the repetitive inspection

requirements of paragraph (e)(2) of this AD.

(f) For airplanes with serial numbers listed in Airbus Service

Bulletin A300-53-100, Revision 1, dated May 10, 1984: Perform an

internal and external visual inspection to detect cracks of the

longitudinal joint at stringer 51 (left- and right-hand) between

frames 72 and 80, in accordance with the Accomplishment Instructions

of the service bulletin, and in accordance with the times specified

in this paragraph.

(1) Perform the initial inspection at the later of the times

specified in paragraph (f)(1)(i) or (f)(1)(ii) of this AD:

(i) Prior to the accumulation of 12,000 total landings or 15,000

total flight hours, whichever occurs earlier; or

(ii) Within one year after September 26, 1986.

(2) If no crack is found, repeat the internal inspection

thereafter at intervals not to exceed 1,500 flight hours, and repeat

the external inspection thereafter at intervals not to exceed 12,000

flight hours.

(3) If any crack is detected, prior to further flight, repair it

in accordance with the service bulletin.

(4) Installation of Airbus Modification 1421 (reference Airbus

Service Bulletin A300-53-033, Revision 3, dated May 10, 1984)

constitutes terminating action for the repetitive inspection

requirements of paragraph (f)(2) of this AD.

(g) For airplanes with serial numbers listed in Airbus Service

Bulletin A300-55-026, Revision 3, dated May 10, 1984: Perform a

visual inspection of the 6 vertical stabilizer attachment fittings

for cracks, which initiate from the rivet holes, in accordance with

the Accomplishment Instructions of the service bulletin, and in

accordance with the times specified in this paragraph.

(1) Perform the initial inspection at the later of the times

specified in paragraph (g)(1)(i) or (g)(1)(ii) of this AD:

(i) Prior to the accumulation of 20,000 total landings or 20,000

total flight hours, whichever occurs earlier; or

(ii) Within one year after September 26, 1986, whichever occurs

earlier.

(2) If no crack is detected, repeat the inspection thereafter at

intervals not to exceed 1,500 landings.

(3) If any crack is detected, prior to further flight, repair it

in accordance with the service bulletin.

(4) Installation of Airbus Modification 3172 (reference Airbus

Service Bulletin A300-55-024, Revision 4, dated May 25, 1984)

constitutes terminating action for the repetitive inspection

requirements of paragraph (g)(2) of this AD.

(h) For airplanes with serial numbers listed in Airbus Service

Bulletin A300-57-109, Revision 1, dated July 10, 1982: Perform a

visual inspection to detect cracks in the landing angle attached to

the outboard side of the wing leading edge at nose rib 8 (left- and

right-hand), in accordance with the Accomplishment Instructions of

the service bulletin, and in accordance with the times specified in

this paragraph.

(1) Perform the initial inspecton at the later of the times

specified in paragraph (h)(1)(i) or (h)(1)(ii):

(i) Prior to the accumulation of 15,000 total landings; or

[[Page 18704]]

(ii) Within one year after September 26, 1986.

(2) If no crack is detected, repeat the inspection thereafter at

intervals not to exceed 3,000 landings.

(3) If any crack is detected, within the next 1,000 landings

following crack detection, install Airbus Modification 1307 in

accordance with Airbus Service Bulletin A300-57-026, Revision 3,

dated October 21, 1982.

(4) Installation of Airbus Modification 1307 (reference Airbus

Service Bulletin A300-57-026, Revision 3, dated October 21, 1982)

constitutes terminating action for the repetitive inspection

requirements of paragraph (h)(2) of this AD.

(i) Special flight permits may be issued in accordance with

sections 21.197 and 21.199 of the Federal Aviation Regulations (14

CFR 21.197 and 21.199) to operate the airplane to a location where

the requirements of this AD can be accomplished.

(j) An alternative method of compliance or adjustment of the

compliance time that provides an acceptable level of safety may be

used if approved by the Manager, Standardization Branch, ANM-113,

FAA, Transport Airplane Directorate. Operators shall submit their

requests through an appropriate FAA Principal Maintenance Inspector,

who may add comments and then send it to the Manager,

Standardization Branch, ANM-113.

Note 3: Information concerning the existence of approved

alternative methods of compliance with this AD, if any, may be

obtained from the Standardization Branch, ANM-113.

Issued in Renton, Washington, on April 23, 1996.

S.R. Miller,

Acting Manager, Transport Airplane Directorate, Aircraft Certification

Service.

[FR Doc. 96-10508 Filed 4-26-96; 8:45 am]

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