Airworthiness Directives; Airbus Model A300, A310, and A300-600 Series Airplanes

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-187-AD; Amendment 39-10840; AD 98-21-32]

RIN 2120-AA64

Airworthiness Directives; Airbus Model A300, A310, and A300-600

Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: This amendment supersedes an existing airworthiness directive

(AD), applicable to all Airbus Model A300, A310, and A300-600 series

airplanes, that currently requires performing a ram air turbine (RAT)

extension test; removing and disassembling the RAT uplock mechanism;

performing an inspection to detect corrosion of the RAT uplock

mechanism, and replacement with a new assembly, if necessary; and

cleaning all the parts of the RAT control shaft and its bearing

component parts. This amendment requires modification of the RAT

unlocking control unit, which constitutes terminating action for the

repetitive tests and inspections. This amendment also limits the

applicability of the existing AD. This amendment is prompted by

issuance of mandatory continuing airworthiness information by a foreign

civil airworthiness authority. The actions specified by this AD are

intended to prevent corrosion of the RAT uplock pin/shaft and needle,

which could result in failure of the RAT to deploy and consequent loss

of emergency hydraulic power to the flight controls in the event that

power is lost in both engines.

DATES: Effective November 20, 1998.

The incorporation by reference of certain publications listed in

the regulations is approved by the Director of the Federal Register as

of November 20, 1998.

The incorporation by reference of certain other publications, as

listed in the regulations, was approved previously by the Director of

the Federal Register as of December 2, 1997 (62 FR 55726, October 28,

1997).

ADDRESSES: The service information referenced in this AD may be

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

Blagnac Cedex, France. This information may be examined at the Federal

Aviation Administration (FAA), Transport Airplane Directorate, Rules

Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of

the Federal Register, 800 North Capitol Street, NW., suite 700,

Washington, DC.

FOR FURTHER INFORMATION CONTACT: Norman B. Martenson, Manager,

International Branch, ANM-116, FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)

227-2110; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) by superseding AD 97-22-06,

amendment 39-10177 (62 FR 55726, October 28, 1997), which is applicable

to all Airbus Model A300, A310, and A300-600 series airplanes, was

published in the Federal Register on August 13, 1998 (63 FR 43349). The

action proposed to continue to require performing a ram air turbine

(RAT) extension test; removing and disassembling the RAT uplock

mechanism; performing an inspection to detect corrosion of the RAT

uplock mechanism, and replacement with a new assembly, if necessary;

and cleaning all the parts of the RAT control shaft and its bearing

component parts. The action also proposed to require modification of

the RAT unlocking control unit, which constitutes terminating action

for the repetitive tests and inspections. Additionally, the action

proposed to limit the applicability of the existing AD.

Comments

Interested persons have been afforded an opportunity to participate

in the making of this amendment. Due consideration has been given to

the single comment received.

The commenter supports the proposed rule.

Explanation of Correction Made to This Final Rule

In paragraph (a) of the proposed rule, the FAA inadvertently

referenced Airbus Service Bulletins A300-29-0108, dated April 1, 1996;

A310-29-2076, dated April 1, 1996; and A300-29-6037, dated April 1,

1996; for accomplishment of the action required by paragraph (a)(1) of

the NPRM. However, the Airplane Maintenance Manual is the correct

reference for accomplishment of the action required by paragraph

(a)(1). Paragraph (a) of this final rule has been revised accordingly.

Conclusion

After careful review of the available data, including the comment

noted above, the FAA has determined that air safety and the public

interest require the adoption of the rule with the change previously

described. The FAA has determined that this change will neither

increase the economic burden on any operator nor increase the scope of

the AD.

Cost Impact

There are approximately 126 Model A300, A310, and A300-600 series

airplanes of U.S. registry that will be affected by this AD.

The actions that are currently required by AD 97-22-06, and

retained in this AD, take approximately 10 work hours per airplane to

accomplish, at an average labor rate of $60 per work hour. Required

parts will be provided by the manufacturer at no cost to the operators.

Based on these figures, the cost impact of the previously required

actions on U.S. operators is estimated to be $75,600, or $600 per

airplane.

The new modification that is required in this AD action will take

approximately 9 work hours per airplane to accomplish, at an average

[[Page 55521]]

labor rate of $60 per work hour. Required parts will cost approximately

$1,972 per airplane. Based on these figures, the cost impact of the

modification required by this AD on U.S. operators is estimated to be

$316,512, or $2,512 per airplane.

The cost impact figures discussed above are based on assumptions

that no operator has yet accomplished any of the 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 adopted herein will 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 final

rule does not have sufficient federalism implications to warrant the

preparation of a Federalism Assessment.

For the reasons discussed above, I certify that this action (1) is

not a ``significant regulatory action'' under Executive Order 12866;

(2) is not a ``significant rule'' under DOT Regulatory Policies and

Procedures (44 FR 11034, February 26, 1979); and (3) 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 final evaluation has been prepared for this action

and it is contained in the Rules Docket. A copy of it may be obtained

from the Rules Docket at the location provided under the caption

ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by

reference, Safety.

Adoption of the Amendment

Accordingly, pursuant to the authority delegated to me by the

Administrator, the Federal Aviation Administration amends 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 39-10177 (62 FR

55726, October 28, 1997), and by adding a new airworthiness directive

(AD), amendment 39-10840, to read as follows:

98-21-32 Airbus Industrie: Amendment 39-10840. Docket 98-NM-187-AD.

Supersedes AD 97-22-06, Amendment 39-10177.

Applicability: Model A300, A310, and A300-600 series airplanes

on which Airbus Modification 11527 has not been accomplished;

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 (d) 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.

Compliance: Required as indicated, unless accomplished

previously.

To prevent corrosion of the ram air turbine (RAT) uplock pin/

shaft and needle, which could result in failure of the RAT to deploy

and consequent loss of emergency hydraulic power to the flight

controls in the event that power is lost in both engines, accomplish

the following:

Restatement of the Requirements of AD 97-22-06

(a) Within 30 months since the date of manufacture, or within 3

months after December 2, 1997 (the effective date of AD 97-22-06,

amendment 39-10177), whichever occurs later, accomplish the

requirements of paragraphs (a)(1) and (a)(2) of this AD. Thereafter,

repeat these actions at intervals not to exceed 30 months.

(1) Perform a RAT extension test on the ground, in accordance

with the procedures specified in the Airplane Maintenance Manual.

(2) Disassemble and remove the uplock mechanism of the RAT and

perform a visual inspection of the uplock mechanism to detect

corrosion, in accordance with Airbus Service Bulletin A300-29-0108,

dated April 1, 1996 (for Model A300 series airplanes); A310-29-2076,

dated April 1, 1996 (for Model A310 series airplanes); or A300-29-

6037, dated April 1, 1996 (for Model A300-600 series airplanes); as

applicable.

Note 2: For the purposes of this AD, the RAT uplock mechanism

includes both the lever assembly and uplock unit.

(i) If no corrosion is detected: Prior to further flight, clean

and lubricate the uplock mechanism and its associated parts,

reinstall the assembly, and perform a retraction/extension/

retraction of the RAT, in accordance with the applicable service

bulletin.

(ii) If any corrosion is detected in any part of the uplock

mechanism, prior to further flight, accomplish either paragraph

(a)(2)(ii)(A) or (a)(2)(ii)(B) of this AD in accordance with the

applicable service bulletin.

(A) Replace the uplock mechanism with a new part and perform a

retraction/extension/retraction of the RAT, in accordance with the

applicable service bulletin. Or

(B) Clean and lubricate the uplock mechanism and its associated

parts. Within 30 days following accomplishment of this cleaning and

lubrication, replace the uplock mechanism with a new part and

perform a retraction/extension/retraction of the RAT.

(b) Initial accomplishment of the actions required by paragraph

(a) of this AD that have been performed in accordance with Airbus

All Operator Telex 29-16, Revision 01, dated January 10, 1996, is

considered acceptable for compliance with the initial RAT extension

test and an initial visual inspection as required by paragraph (a)

of this AD. However, the first repetitive inspection, as required by

paragraph (a) of this AD, must be performed within 30 months after

that RAT extension test and visual inspection were conducted, and

repeated thereafter at intervals not to exceed 30 months.

New Requirements of This AD

(c) Within 30 months after the effective date of this AD, modify

the RAT unlocking control unit in accordance with Airbus Service

Bulletin A300-29-0109 (for Model A300 series airplanes); A310-29-

2077 (for Model A310 series airplanes); or A300-29-6038 (for Model

A300-600 series airplanes); all dated January 27, 1997; as

applicable. Accomplishment of this modification constitutes

terminating action for the repetitive test and inspection

requirements of this AD.

(d) 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, International Branch, ANM-116, 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, International

Branch, ANM-116.

Note 3: Information concerning the existence of approved

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

obtained from the International Branch, ANM-116.

(e) 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.

(f) Except as provided by paragraph (a)(1) of this AD, the

actions shall be done in accordance with Airbus Service Bulletin

A300-29-0108, dated April 1, 1996; Airbus Service Bulletin A310-29-

2076, dated April 1, 1996; Airbus Service Bulletin A300-29-6037,

dated April 1, 1996; Airbus Service Bulletin A300-29-0109, dated

January 27, 1997; Airbus Service Bulletin A310-29-2077, dated

January 27, 1997; and Airbus Service Bulletin A300-29-6038; dated

January 27, 1997; as applicable.

[[Page 55522]]

(1) The incorporation by reference of Airbus Service Bulletin

A300-29-0109, dated January 27, 1997; Airbus Service Bulletin A310-

29-2077, dated January 27, 1997; and Airbus Service Bulletin A300-

29-6038; dated January 27, 1997; is approved by the Director of the

Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part

51.

(2) The incorporation by reference of Airbus Service Bulletin

A300-29-0108, dated April 1, 1996; Airbus Service Bulletin A310-29-

2076, dated April 1, 1996; and Airbus Service Bulletin A300-29-6037,

dated April 1, 1996; was approved previously by the Director of the

Federal Register as of December 2, 1997 (62 FR 55726, October 28,

1997).

(3) Copies may be obtained from Airbus Industrie, 1 Rond Point

Maurice Bellonte, 31707 Blagnac Cedex, France. Copies may be

inspected at the FAA, Transport Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington; or at the Office of the Federal

Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

Note 4: The subject of this AD is addressed in French

airworthiness directive 95-163-182(B)R3, dated May 7, 1997.

(g) This amendment becomes effective on November 20, 1998.

Issued in Renton, Washington, on October 7, 1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane Directorate, Aircraft Certification

Service.

[FR Doc. 98-27482 Filed 10-15-98; 8:45 am]

BILLING CODE 4910-13-U