Airworthiness Directives; McDonnell Douglas Model DC-9 and C-9 (Military) Series Airplanes

[Federal Register Volume 64, Number 106 (Thursday, June 3, 1999)]
[Rules and Regulations]
[Pages 29777-29778]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-12829]



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Federal Register / Vol. 64, No. 106 / Thursday, June 3, 1999 / Rules 
and Regulations

[[Page 29777]]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-110-AD; Amendment 39-11177; AD 99-08-05 R1]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model DC-9 and C-9 
(Military) Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; correction.

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SUMMARY: This amendment corrects information in an existing 
airworthiness directive (AD), applicable to certain McDonnell Douglas 
Model DC-9 and C-9 (military) series airplanes, that currently requires 
repetitive inspections to detect fatigue cracking of the fuselage 
frames and longerons 16R and 17R above the forward lower cargo door; 
repair, if necessary; and modification of the fuselage frames and 
longerons, if necessary, and follow-on repetitive inspections to detect 
fatigue cracking of the skin adjacent to the modification. That AD was 
prompted by numerous instances of fatigue cracking of the fuselage 
frames and longerons. The actions specified by that AD are intended to 
prevent fatigue cracking of the fuselage frames and longerons 16R and 
17R, which could result in reduced structural integrity of the 
airplane. This amendment corrects an erroneous reference to a certain 
volume of the Supplemental Inspection Document.

DATES: Effective May 12, 1999.
    The incorporation by reference of McDonnell Douglas Service 
Bulletin DC9-53-267, dated October 20, 1997, was approved previously by 
the Director of the Federal Register as of May 12, 1999 (64 FR 16805, 
April 7, 1999).

ADDRESSES: The service information referenced in this AD may be 
obtained from The Boeing Commercial Aircraft Group, Douglas Products 
Division, 3855 Lakewood Boulevard, Long Beach, California 90846, 
Attention: Technical Publications Business Administration, Dept. C1-L51 
(2-60). 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 FAA, Transport 
Airplane Directorate, Los Angeles Aircraft Certification Office, 3960 
Paramount Boulevard, Lakewood, California; or at the Office of the 
Federal Register, 800 North Capitol Street, NW., suite 700, Washington, 
DC.

FOR FURTHER INFORMATION CONTACT: Wahib Mina, Aerospace Engineer, 
Airframe Branch, ANM-120L, FAA, Transport Airplane Directorate, Los 
Angeles Aircraft Certification Office, 3960 Paramount Boulevard, 
Lakewood, California 90712-4137; telephone (562) 627-5324; fax (562) 
627-5210.

SUPPLEMENTARY INFORMATION: On March 30, 1999, the Federal Aviation 
Administration (FAA) issued AD 99-08-05, amendment 39-11110 (64 FR 
16805, April 7, 1999), which applies to certain McDonnell Douglas Model 
DC-9 and C-9 (military) series airplanes. That AD requires repetitive 
inspections to detect fatigue cracking of the fuselage frames and 
longerons 16R and 17R above the forward lower cargo door; repair, if 
necessary; and modification of the fuselage frames and longerons, if 
necessary, and follow-on repetitive inspections to detect fatigue 
cracking of the skin adjacent to the modification. That AD was prompted 
by numerous instances of fatigue cracking of the fuselage frames and 
longerons. The actions required by that AD are intended to prevent 
fatigue cracking of the fuselage frames and longerons 16R and 17R, 
which could result in reduced structural integrity of the airplane.
    AD 99-08-05 contains an error in paragraph (d) of the AD. That 
paragraph contains a reference to McDonnell Douglas Model DC-9 
Supplemental Inspection Document, Report No. L26-008, Section 2 of 
Volume III-95, dated September 1995. The correct reference is McDonnell 
Douglas Model DC-9 Supplemental Inspection Document, Report No. L26-
008, Section 2 of Volume I, Revision 5, dated July 1997.
    Action is taken herein to correct the error in AD 99-08-05 and to 
correctly add the AD as an amendment to Sec. 39.13 of the Federal 
Aviation Regulations (14 CFR 39.13).
    The final rule is being reprinted in its entirety for the 
convenience of affected operators. The effective date remains May 12, 
1999.
    Since this action only corrects an error, it has no adverse 
economic impact and imposes no additional burden on any person. 
Therefore, notice and public procedures hereon are unnecessary.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Correction

    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 39-11110 (64 FR 
16805, April 7, 1999), and by adding a new airworthiness directive 
(AD), amendment 39-11177, to read as follows:

99-08-05 R1  McDonnell Douglas: Amendment 39-11177. Docket 98-NM-
110-AD. Revises AD 99-08-05, Amendment 39-11110.

    Applicability: Model DC-9 and C-9 (military) series airplanes, 
as listed in McDonnell Douglas Service Bulletin DC9-53-267, dated 
October 20, 1997; certificated in any category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
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 (e) 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

[[Page 29778]]

been eliminated, the request should include specific proposed 
actions to address it.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent fatigue cracking of the fuselage frames and longerons 
16R and 17R, which could result in reduced structural integrity of 
the airplane, accomplish the following:
    (a) Prior to the accumulation of 30,000 total landings, or 
within 3,000 landings after the effective date of this AD, whichever 
occurs later, perform a visual inspection to detect fatigue cracking 
of the fuselage frames and longerons 16R and 17R above the forward 
lower cargo door, in accordance with paragraph 3.B.1. of the 
Accomplishment Instructions of McDonnell Douglas Service Bulletin 
DC9-53-267, dated October 20, 1997.
    (b) Condition 1. If no cracking is detected during the 
inspection required by paragraph (a) of this AD, accomplish the 
requirements of either paragraph (b)(1) or (b)(2) of this AD, in 
accordance with McDonnell Douglas Service Bulletin DC9-53-267, dated 
October 20, 1997.
    (1) Option 1. Repeat the visual inspection required by paragraph 
(a) of this AD thereafter at intervals not to exceed 19,000 
landings. Or
    (2) Option 2. Prior to further flight, modify the fuselage 
frames and longerons 16R and 17R. Prior to the accumulation of 
19,000 landings after accomplishment of the modification, perform 
the visual inspection specified in paragraph 3.B.1.D. of the 
Accomplishment Instructions of the service bulletin to detect 
fatigue cracking of the skin adjacent to the modification.
    (i) If no cracking is detected, repeat the visual inspection 
thereafter at intervals not to exceed 19,000 landings.
    (ii) If any cracking is detected, prior to further flight, 
repair in accordance with a method approved by the Manager, Los 
Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane 
Directorate.
    (c) Condition 2. If any cracking is detected during the 
inspection required by paragraph (a) of this AD, prior to further 
flight, repair the cracked area and modify the fuselage frames and 
longerons 16R and 17R; in accordance with McDonnell Douglas Service 
Bulletin DC9-53-267, dated October 20, 1997. Prior to the 
accumulation of 19,000 landings after accomplishment of the 
modification, perform the visual inspection specified in paragraph 
3.B.1.D.(5) of the Accomplishment Instructions of the service 
bulletin to detect fatigue cracking of the skin adjacent to the 
modification, in accordance with the service bulletin.
    (1) If no cracking is detected, repeat the visual inspection 
thereafter at intervals not to exceed 19,000 landings.
    (2) If any cracking is detected, prior to further flight, repair 
in accordance with a method approved by the Manager, Los Angeles 
ACO.
    (d) Accomplishment of the inspections required by this AD 
constitutes terminating action for the inspections of Principal 
Structural Element 53.09.055A (reference McDonnell Douglas Model DC-
9 Supplemental Inspection Document, Report No. L26-008, Section 2 of 
Volume I, Revision 5, dated July 1997), as required by AD 96-13-03, 
amendment 39-9671.

Alternative Methods of Compliance

    (e) 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, Los Angeles ACO. Operators shall 
submit their requests through an appropriate FAA Principal 
Maintenance Inspector, who may add comments and then send it to the 
Manager, Los Angeles ACO.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Los Angeles ACO.

Special Flight Permits

    (f) 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.

Incorporation by Reference

    (g) Except as provided by paragraphs (b)(2)(ii) and (c)(2) of 
this AD, the actions shall be done in accordance with McDonnell 
Douglas Service Bulletin DC9-53-267, dated October 20, 1997. The 
incorporation by reference of this document was approved previously 
by the Director of the Federal Register as of May 12, 1999 (64 FR 
16805, April 7, 1999). Copies may be obtained from Boeing Commercial 
Aircraft Group, Douglas Products Division, 3855 Lakewood Boulevard, 
Long Beach, California 90846, Attention: Technical Publications 
Business Administration, Dept. C1-L51 (2-60). Copies may be 
inspected at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue, SW., Renton, Washington; or at the FAA, Transport Airplane 
Directorate, Los Angeles Aircraft Certification Office, 3960 
Paramount Boulevard, Lakewood, California; or at the Office of the 
Federal Register, 800 North Capitol Street, NW., suite 700, 
Washington, DC.
    (h) The effective date of this amendment remains May 12, 1999.

    Issued in Renton, Washington, on May 14, 1999.
Donald E. Gonder,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 99-12829 Filed 6-2-99; 8:45 am]
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