Airworthiness Directives; McDonnell Douglas Model DC-8 Series Airplanes Modified in Accordance With Supplemental Type Certificate SA1802SO

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-379-AD; Amendment 39-11016; AD 98-26-51]

RIN 2120-AA64

Airworthiness Directives; McDonnell Douglas Model DC-8 Series

Airplanes Modified in Accordance With Supplemental Type Certificate

SA1802SO

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This document publishes in the Federal Register an amendment

adopting Airworthiness Directive (AD) 98-26-51 that was sent previously

to all known U.S. owners and operators of certain McDonnell Douglas

Model DC-8 series airplanes by individual telegrams. This AD requires a

revision to the Airplane Flight Manual to specify restrictions on

operating if any pressurization anomaly is detected. This AD also

requires a one-time inspection to detect discrepancies and cracking of

the main deck cargo door in the immediate area of the bolts attaching

the latch fittings, and repair, if necessary. This action is prompted

by a report that a cabin pressurization anomaly was detected on a

McDonnell Douglas Model DC-8 series airplane, and by subsequent

investigation, which revealed fatigue cracking in the structure of the

main deck cargo door. The actions specified by this AD are intended to

detect and correct fatigue cracking in the structure of the main deck

cargo door, which could result in cabin decompression of the airplane

and loss of the main deck cargo door, and consequent reduced

controllability of the airplane.

DATES: Effective February 3, 1999, to all persons except those persons

to whom it was made immediately effective by telegraphic AD T98-26-51,

issued December 18, 1998, which contained the requirements of this

amendment.

Comments for inclusion in the Rules Docket must be received on or

before March 30, 1999.

ADDRESSES: Submit comments in triplicate to the Federal Aviation

Administration (FAA), Transport Airplane Directorate, ANM-114,

Attention: Rules Docket No. 98-NM-379-AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055-4056.

Information pertaining to this amendment may be obtained from or

examined at the FAA, Transport Airplane Directorate, 1601 Lind Avenue,

SW., Renton, Washington 98055-4056; or at the FAA, Small Airplane

Directorate, Atlanta Aircraft Certification Office, One Crown Center,

1895 Phoenix Boulevard, suite 450, Atlanta, Georgia 30337-2748.

FOR FURTHER INFORMATION CONTACT: Rany Azzi, Aerospace Engineer,

Airframe and Propulsion Branch, ACE-117A, FAA, Small Airplane

Directorate, Atlanta Aircraft Certification Office, One Crown Center,

1895 Phoenix Boulevard, Suite 450, Atlanta, Georgia 30337-2748;

telephone (770) 703-6080; fax (770) 703-6097.

SUPPLEMENTARY INFORMATION: On December 18, 1998, the FAA issued

telegraphic AD T98-26-51, which is applicable to certain McDonnell

Douglas Model DC-8 series airplanes

[[Page 4524]]

modified in accordance with Supplemental Type Certificate (STC)

SA1802SO. That action was prompted by a report indicating that a cabin

pressurization anomaly was detected on a McDonnell Douglas Model DC-8

series airplane modified in accordance with STC SA1802SO. Investigation

revealed fatigue cracking in the structure of the main deck cargo door.

Propagation of cracks on the frames and inner skin of the latch fitting

supports could lead to severed frames and inner skin at the latch

fitting supports of the main deck cargo door. This condition, if not

corrected, could result in cabin decompression of the airplane and loss

of the main deck cargo door, and consequent reduced controllability of

the airplane.

Explanation of Requirements of the Rule

Since the unsafe condition described is likely to exist or develop

on other airplanes of the same type design, the FAA issued telegraphic

AD T98-26-51 to detect and correct fatigue cracking in the structure of

the main deck cargo door, which could result in cabin decompression of

the airplane and loss of the main deck cargo door, and consequent

reduced controllability of the airplane. The AD requires a revision to

the FAA-approved Airplane Flight Manual to specify restrictions on

operating if any pressurization anomaly is detected. The AD also

requires a one-time detailed visual inspection to detect discrepancies

and cracking of the main deck cargo door in the immediate area of the

bolts attaching the latch fittings, and repair, if necessary.

Interim Action

This is considered to be interim action until final action is

identified, at which time the FAA may consider further rulemaking.

Since it was found that immediate corrective action was required,

notice and opportunity for prior public comment thereon were

impracticable and contrary to the public interest, and good cause

existed to make the AD effective immediately by individual telegrams

issued on December 18, 1998, to all known U.S. owners and operators of

McDonnell Douglas Model DC-8 series airplanes modified in accordance

with STC SA1802SO. These conditions still exist, and the AD is hereby

published in the Federal Register as an amendment to section 39.13 of

the Federal Aviation Regulations (14 CFR 39.13) to make it effective to

all persons.

Comments Invited

Although this action is in the form of a final rule that involves

requirements affecting flight safety and, thus, was not preceded by

notice and an opportunity for public comment, comments are invited on

this rule. Interested persons are invited to comment on this 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 under the caption ADDRESSES. All

communications received on or before the closing date for comments will

be considered, and this rule may be amended in light of the comments

received. Factual information that supports the commenter's ideas and

suggestions is extremely helpful in evaluating the effectiveness of the

AD action and determining whether additional rulemaking action would be

needed.

Comments are specifically invited on the overall regulatory,

economic, environmental, and energy aspects of the rule that might

suggest a need to modify the 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 that

summarizes each FAA-public contact concerned with the substance of this

AD will be filed in the Rules Docket.

Commenters wishing the FAA to acknowledge receipt of their comments

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

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

to Docket Number 98-NM-379-AD.'' The postcard will be date stamped and

returned to the commenter.

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.

The FAA has determined that this regulation is an emergency

regulation that must be issued immediately to correct an unsafe

condition in aircraft, and that it is not a ``significant regulatory

action'' under Executive Order 12866. It has been determined further

that this action involves an emergency regulation under DOT Regulatory

Policies and Procedures (44 FR 11034, February 26, 1979). If it is

determined that this emergency regulation otherwise would be

significant under DOT Regulatory Policies and Procedures, a final

regulatory evaluation will be prepared and placed in the Rules Docket.

A copy of it, if filed, 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, 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 adding the following new

airworthiness directive:

98-26-51 McDonnell Douglas: Amendment 39-11016. Docket 98-NM-379-

AD.

Applicability: Model DC-8 series airplanes that have been

converted from a passenger-carrying to a cargo-carrying

(``freighter'') configuration in accordance with Supplemental Type

Certificate (STC) SA1802SO.

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 (g) 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 detect and correct fatigue cracking in the structure of the

main deck cargo door, which could result in cabin decompression of

the airplane and loss of the main deck cargo door, and consequent

reduced controllability of the airplane, accomplish the following:

(a) Within 24 hours after the effective date of this AD, revise

the Limitations Section of

[[Page 4525]]

the FAA-approved Airplane Flight Manual (AFM) to include the

following information. This may be accomplished by inserting a copy

of this AD into the AFM.

``IF ANY UNEXPECTED LOSS OF CABIN PRESSURE OCCURS, DO NOT INCREASE

CABIN PRESSURE. IMMEDIATELY SELECT A HIGHER CABIN ALTITUDE AND, AS

SOON AS POSSIBLE, DESCEND TO A LOWER FLIGHT ALTITUDE.''

(b) Except as provided by paragraph (d) of this AD, within 7

days after the effective date of this AD: Perform an internal

detailed visual inspection to detect cracking or any discrepancy of

the main deck cargo door in the immediate area of the bolts

attaching the latch fittings. Inspect for cracking or any

discrepancy of the skin in the immediate area of the fastener heads,

and for loose or missing fasteners. In addition, prior to the

internal detailed visual inspection, clean and degrease the inside

structure where the latch fitting bolts attach to the frames, and

perform a detailed visual inspection of the frames to detect

cracking emanating from the bolt holes and at the bend radius of the

frames.

Note 2: Removal of the inner skin of the main deck cargo door is

not necessary to gain access and inspect for cracking emanating from

the bolt holes and at the bend radius of the frames.

(c) Prior to accomplishment of the inspections required by

paragraph (b) of this AD, notify an appropriate FAA Principal

Maintenance Inspector of the date and time the inspection required

by paragraph (b) of this AD is to be accomplished.

(d) For airplanes on which there have been reports of cabin

pressurization anomalies or illuminations of the main deck cargo

door warning light within 30 days prior to the effective date of

this AD or within 7 days after the effective date of this AD:

Perform the inspection required by paragraph (b) of this AD prior to

further flight.

(e) If any discrepancy is detected during the inspections

required by paragraph (b) of this AD, prior to further flight,

repair in accordance with a method approved by the Manager, Atlanta

Aircraft Certification Office (ACO), FAA, Small Airplane

Directorate.

(f) Within 24 hours after accomplishment of the inspections

required by paragraph (b) of this AD, or within 24 hours after the

effective date of this AD, whichever occurs later, submit a report

of the inspection results (both positive and negative findings) to

the Manager, Atlanta ACO, FAA, Small Airplane Directorate, One Crown

Center, 1895 Phoenix Boulevard, Suite 450, Atlanta, Georgia 30349;

fax (770) 703-6097. Information collection requirements contained in

this regulation have been approved by the Office of Management and

Budget (OMB) under the provisions of the paperwork reduction act of

1980 (44 U.S.C. 3501 et seq.) and have been assigned OMB control

number 2120-0056.

(g) 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, Atlanta ACO. Operators shall submit

their requests through an appropriate FAA Principal Maintenance

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

Atlanta ACO.

Note 3: Information concerning the existence of approved

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

obtained from the Atlanta ACO.

(h) 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.

(i) This amendment becomes effective on February 3, 1999, to all

persons except those persons to whom it was made immediately

effective by telegraphic AD T98-26-51, issued on December 18, 1998,

which contained the requirements of this amendment.

Issued in Renton, Washington, on January 22, 1999.

Darrell M. Pederson,

Acting Manager, Transport Airplane Directorate, Aircraft Certification

Service.

[FR Doc. 99-2107 Filed 1-28-99; 8:45 am]

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