AD 99-08-05 R1

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AD Number:
99-08-05 R1
Document Type:
AD Final Rules
Docket Number:
98-NM-110-AD
Subject Heading:
Airworthiness Directives; McDonnell Douglas Model DC-9 and C-9 (Military) Series Airplanes
Subject:
Fuselage Frames And Longerons
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
05/12/1999
Make:
The Boeing Company
Model:
DC-9-11 | DC-9-12 | DC-9-13 | DC-9-14 | DC-9-15 | DC-9-15F | DC-9-21 | DC-9-31 | DC-9-32 | DC-9-32 (...Show more
Product Type:
Aircraft
Product Subtype:
Large Airplane
Affected AD:
Superseded AD:
Affected By:
Superseded By:
Service/Office:
Office of Primary Responsibility:
CFR Part Reference:
Part 39 (64 FR 29783 No. 106 06/03/99)
Comments:
AIRWORTHINESS DIRECTIVES FINAL RULES: 99-08-05 R1
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   98-NM-110-AD

AMENDMENT:   39-11177

AD NUMBER:   99-08-05 R1

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

ACTION:   Final rule; correction

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.

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).

DATES:   Effective May 12, 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:   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 section 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.

§ 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:

REGULATORY TEXT:  
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 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.

FOOTER: