AD 95-06-05

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AD Number:
95-06-05
Document Type:
AD Final Rules
Docket Number:
95-NM-23-AD
Subject Heading:
Airworthiness Directives; Boeing Model 737-200 and -300 Series Airplanes
Subject:
Fuselage Frame Inspection
Status:
Current
Citation:
(Federal Register: March 21, 1995 (Volume 60, Number 54))
Citation Publish Date:
03/21/1995
Effective Date:
04/05/1995
Make:
The Boeing Company
Model:
737-200 Series | 737-300 Series
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Superseded AD: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Superseded By: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 (60 FR 14897 NO. 54 3/21/95)
Comments:
Updated RGL applicability to match AD applicability; CAR C-11-185
AIRWORTHINESS DIRECTIVES FINAL RULES: 95-06-05
CITATION:   [Federal Register: March 21, 1995 (Volume 60, Number 54)]

PAGE NUMBER:   [Page 14897]

DOCKET NUMBER:   95-NM-23-AD

AMENDMENT:   39-9175

AD NUMBER:   95-06-05

SUBJECT HEADING:   Airworthiness Directives; Boeing Model 737-200 and -300 Series Airplanes

ACTION:   Final rule; request for comments

SUMMARY:  
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 737-200 and -300 series airplanes. This action requires inspections to detect cracking of the fuselage frames at certain locations below the lower jamb of the upper deck main cargo door, and repair, if necessary. This amendment is prompted by reports of fatigue cracking in the fuselage frames at these locations. The actions specified in this AD are intended to prevent rapid decompression of the airplane due to fatigue cracking in the fuselage frames of the main deck cargo door.

DATES:   Effective April 5, 1995. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of April 5, 1995. Comments for inclusion in the Rules Docket must be received on or before May 22, 1995.

ADDRESSES:  
Submit comments in triplicate to the Federal Aviation Administration (FAA),
Transport Airplane Directorate, ANM-103, Attention: Rules Docket No. 95-NM-23-AD, 1601 Lind Avenue, SW., Renton, Washington 98055-4056.

The service information referenced in this AD may be obtained from Pemco Aeroplex,
Incorporated, P.O. Box 2287, Birmingham, Alabama 35201-2287. This information may be
examined at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Small Airplane Directorate, Atlanta Aircraft Certification Office, Campus Building, 1701 Columbia Avenue, Suite 2-160, College Park, Georgia; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:  
Curtis Jackson, Aerospace Engineer, Airframe Branch, ACE-120A, FAA, Small Airplane Directorate, Atlanta Aircraft Certification Office, Campus Building, 1701 Columbia Avenue, Suite 2-160, College Park, Georgia 30337-2748; telephone (404) 305-7348; fax (404); 305-7348; or Della Swartz, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Transport Airplane Directorate, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206) 227-2785; fax (206) 227-1181.

SUPPLEMENTARY INFORMATION:  
Recently, two operators reported finding fatigue cracks in the fuselage frames below the lower jamb of the main deck cargo door between stringers 20L and 21L at water line 180 on Boeing Model 737-300 series airplanes. The cracking was randomly located in various areas of the fuselage frames and may have initiated at frame stations 380, 400, 420, 440, 460, and/or 480 at the radius of the frame webs that were modified in accordance with supplemental type certificate (STC) SA2969SO.

Such cracking, if not detected and corrected in a timely manner, could result in rapid decompression of the airplane.

Pemco Aeroplex installed main deck cargo doors on Boeing Model 737-200 and -300 series airplanes in accordance with STC SA2969SO. Therefore, the FAA has determined that Boeing Model 737-200 series airplanes are also subject to the same unsafe condition.

The FAA has reviewed and approved Pemco Alert Service Letter 737-53-0004, dated January 10, 1995, which describes procedures for detailed close visual inspections to detect cracking of the fuselage frames below the lower jamb of the upper deck main cargo door between stringers 20L and 21L at water line 180 at frame stations 380, 400, 420, 440, 460, and 480, and repair of any cracking found.

Since an unsafe condition has been identified that is likely to exist or develop on other airplanes of the same type design, this AD is being issued to prevent rapid decompression of the airplane due to cracking of the fuselage frames below the lower jamb of the upper deck main cargo door. This AD requires detailed close visual inspections to detect cracking of the fuselage frames below the lower jamb of the upper deck main cargo door, and repair, if necessary. The actions are required to be accomplished in accordance with the alert service letter described previously.

This is considered to be interim action until final action is identified, at which time the FAA may consider further rulemaking.

[NOTE: The FAA previously issued AD 95-01-06, amendment 39-9117 (60 FR 2323, January 9, 1995), which is applicable to the same airplanes affected by this new AD action. AD 95-01-06 requires inspections to detect cracking in the radii on the support angles on the lower jamb (latch lug fittings) of the main cargo door, and replacement of cracked parts. The requirements of AD 95-01-06 are different and separate from the requirements of this new AD.]

As a result of recent communications with the Air Transport Association (ATA) of America, the FAA has learned that, in general, some operators may misunderstand the legal effect of AD's on airplanes that are identified in the applicability provision of the AD, but that have been altered or repaired in the area addressed by the AD. The FAA points out that all airplanes identified in the applicability provision of an AD are legally subject to the AD. If an airplane has been altered or repaired in the affected area in such a way as to affect compliance with the AD, the owner or operator is required to obtain FAA approval for an alternative method of compliance with the AD, in accordance with the paragraph of each AD that provides for such approvals. A note has been included in this rule to clarify this long-standing requirement.

Since a situation exists that requires the immediate adoption of this regulation, it is found that notice and opportunity for prior public comment hereon are impracticable, and that good cause exists for making this amendment effective in less than 30 days.

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 95-NM-23-AD." The postcard will be date stamped and returned to the commenter.

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, 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. App. 1354(a), 1421 and 1423; 49 U.S.C. 106(g); and 14 CFR 11.89. § 39.13 - [Amended]

2. Section 39.13 is amended by adding the following new airworthiness directive:

REGULATORY TEXT:  
95-06-05 BOEING: Amendment 39-9175. Docket 95-NM-23-AD.

Applicability: Model 737-200 and -300 series airplanes equipped with main deck cargo doors installed in accordance with supplemental type certificate (STC) SA2969SO, 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 use the authority provided in paragraph (b) to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition; or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any airplane from the applicability of this AD.

Compliance: Required as indicated, unless accomplished previously.

To prevent rapid decompression due to cracking of the fuselage frames below the lower jamb of the upper deck main cargo door, accomplish the following:

(a) Within 50 flight cycles after the effective date of this AD or within 50 flight cycles after the installation of STC SA2969SO, whichever occurs later, perform a detailed close visual inspection to detect cracking of the fuselage frames below the lower jamb of the upper deck main cargo door between stringers 20L and 21L at water line 180 at frame stations 380, 400, 420, 440, 460, and 480, in accordance with Pemco Alert Service Letter 737-53-0004, dated January 10, 1995.

(1) If no cracking is detected, repeat the visual inspection thereafter at intervals not to exceed 450 flight cycles until the repair described in Pemco Alert Service Letter 737-53-0004, dated January 10, 1995, has been accomplished.

(2) If any cracking is detected, prior to further flight, repair in accordance with Pemco Alert Service Letter 737-53-0004, dated January 10, 1995.

(b) 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, FAA, Small Airplane Directorate, Atlanta Aircraft Certification Office (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 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Atlanta ACO.

(c) 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.

(d) The inspections and repair shall be done in accordance with Pemco Alert Service Letter 737-53-0004, including Appendices I and II dated January 10, 1995. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Pemco Aeroplex, Incorporated, P.O. Box 2287, Birmingham, Alabama 35201-2287. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Small Airplane Directorate, Atlanta Aircraft Certification Office, Campus Building, 1701 Columbia Avenue, Suite 2-160, College Park, Georgia; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

(e) This amendment becomes effective on April 5, 1995.

FOOTER: