1 [Federal Register: November 28, 2008 (Volume 73, Number 230)] [Rules and Regulations] [Page 72320-72323] From the Federal Register Online via GPO Access [wais.access.gpo.gov] [DOCID:fr28no08-6]

––––––––––––––––––––––––––––––––––

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0176; Directorate Id entifier 2007-NM-228-AD; Amendment 39-15748; AD 2008-24-08]

RIN 2120-AA64

Airworthiness Directives; Boeing Model 737- 600, -700, -700C, -800 and -900 Series Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

––––––––––––––––––––––––––––––––––

SUMMARY: We are adopting a new airworthiness dir ective (AD) for certain Boeing Model 737- 600, -700, -700C, -800 and -900 series airplanes. This AD requires an inspecti on of the escape slides for the forward and aft entry and service doors to determine the part number and service bulletin number stenciled on the escape slide girt, and modi fication of the escape slide assemblies. This AD also requires concurrent modifica tion of the escape slide latch asse mblies; concurrent inspection of the escape slides to determine the part number a nd service bulletin number stenciled on the escape slide girts, and replacement of the trigger housin g on the regulator valve with an improved trigger housing if necessary; and concurrent replacement of the rod in the pilot valve regulator with a new, improved rod; as applicable. This AD results fr om reports that certai n escape slides did not automatically inflate when deployed or after the manual inflation cable was pulled. We are issuing this AD to prevent failure of an escape slide to inflate when deployed, which could result in the slide being unusable during an emergency evacuation and consequent injury to passengers or
crewmembers.

DATES: This AD is effective January 2, 2009.
The Director of the Federal Register approved the incorpor ation by reference of certain publications listed in this AD as of January 2, 2009.
The Director of the Federal Register previously approved th e incorporation by reference of Boeing Service Bulletin 737-25-1404, dated May 25, 2000 on August 28, 2001 (66 FR 38361, July 24, 2001).

ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Wash ington 98124-2207; telephone (206) 544-9990; fax (206) 766-5682; email DDCS@boeing.com; Internet https://www.myboeingfleet.com.2 Examining the AD Docket

You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, a ny comments received, and
other information. The address for the Docket Office (telephone 800-647- 5527) is the Document Management Facility, U.S. Department of Trans portation, Docket Operati ons, M-30, West Building Ground Floor, Room W12-140, 1200 New Jers ey Avenue, SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Robert K. Hettman, Aerospace Engineer, Cabin Safety and Environmental Systems Branch, ANM-150S , FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98 057-3356; telephone (425) 917-6457, fax (425) 917-
6590.

SUPPLEMENTARY INFORMATION:

Discussion

We issued a notice of proposed rulemaking (N PRM) to amend 14 CFR part 39 to include an
airworthiness direc tive (AD) that would apply to certain Boeing Model 737-600, -700, -700C, -800 and -900 series airplanes. That NPRM was publis hed in the Federal Register on February 15, 2008 (73 FR 8833). That NPRM proposed to require an in spection of the escape slid es for the forward and aft entry and service doors to determine the part number and service bulletin number stenciled on the escape slide girt, and modification of the escape slide assemblies. That NPRM also proposed to require concurrent modification of the escape slide latch assemblies; concurrent inspection of the escape slides to determine the part number and service bulletin number stenciled on the escape slide girts, and replacement of the trigger housing on the regulator valve with an improved trigger housing if necessary; and concurrent replacement of the rod in the pilot valve regulator with a new, improved rod; as applicable.

Comments

We gave the public the opportunity to particip ate in developing this AD. We considered the
comments received from the three commenters.

Support for the NPRM

Boeing concurs with the cont ents of the proposed rule.

Requests To Refer to Additional Goodrich Service Bulletin

Goodrich, and Air Transport Asso ciation (ATA) on beha lf of one of its members, American Airlines (AA), request that Boeing revise Boeing Service Bulletin 737-25-1491, dated April 23, 2007 (cited in the NPRM as the appropriate source of service information for accomplishing certain actions specified in the NPRM), to include a refe rence to Goodrich Serv ice Bulletin 5A3307-25-339, Revision 2, dated March 31, 2004, as an alternativ e method of compliance (AMOC) to BFGoodrich Service Bulletin 25-308, dated January 21, 2000 (c ited in the NPRM as a source of service information for accomplishing certain other actions specified in the NPRM). ATA and AA note that
this service bulletin modifies the applicable slide to the latest standard offered by Goodrich. AA and Goodrich suggest that if Boeing Service Bulletin 737-25-1491, date d April 23, 2007, is not revised,
the AD should state that it does no t apply to Goodrich part number (P/N) 5A3307-5 slides and that3 Goodrich Service Bulletin 5A3307-25-339, Revision 2, dated March 31, 2004, be identified as an AMOC for the slide portion of the AD. We disagree with the request to revise the AD to refer to Goodrich Service Bulletin 5A3307-25- 339, Revision 2, dated March 31, 2004. There are si gnificant differences in the actions between BFGoodrich Service Bulletin 25-308, dated January 21, 2000 and Goodrich Service Bulletin 5A3307-25-339, Revision 2, dated March 31, 2004. Therefor e, any request to use the procedures in
Goodrich Service Bulletin 5A3307-25-339 is best handled through the AMOC process. Under the provisions of paragraph (k) of the AD, we will c onsider requests for approval of an AMOC if sufficient data are submitted to substantiate that the change would provide an acceptable level of safety. We have not changed the AD in this regard.

Request To Revise Unsafe Condition

Goodrich notes that paragraph (g)(1) of the NPRM addresses an unsafe condition (escape slide latch assembly) that is not mentioned in paragra ph (d), ''Unsafe Condition,'' of the NPRM. Goodrich requests that we revise paragraph (d) to include a reference to the escape slide latch assembly. We disagree with the request to revise the unsafe condition to refer to the escape slide latch assembly. The unsafe condition addr essed by this AD (failure of an escape slide to inflate when deployed) is addressed by the inspection and modi fication required by paragraph (f) of this AD. However, the inspection and modification cannot be done unless the applicable concurrent requirements addressed by both paragraphs (g)(1 ) and (g)(2) of the AD are done before or concurrently with the actions required by paragraph (f) of this AD. Those concurrent requirements, in paragraph (g)(1) of this AD, are pa rt of addressing the unsafe condi tion only in that they enable accomplishment of paragraph (f) of this AD. We have not changed the AD in this regard.

Request To Include Alternative Rod Replacement

Goodrich notes that para graph (g)(3) of the NPRM specifies rod replacement in the regulator
valve in accordance with BFGoodrich Service Bu lletin 25-308, dated January 21, 2000, for slides
with P/Ns 5A3307-1 and -3. Goodrich states that the combination rod/bushing/trigger housing replacement in Goodrich Service Bulletin 5A3307-25-339, Revision 2, dated March 31, 2004, provides an acceptable alternative rod replacement. Goodrich recommends that we include this
alternative in the AD. We disagree with the request to revise the AD to refer to Goodrich Service Bulletin 5A3307-25- 339, Revision 2, dated March 31, 2004. As stated previously, there are significant differences in the
actions between BF Goodrich Service Bulletin 25-308, dated January 21, 2000 and Goodrich Service Bulletin 5A3307-25-339, Revision 2, dated March 31, 2004. Therefore, any request to use the procedures in Goodrich Service Bulletin 5A3307-25- 339 is best handled through the AMOC process. Under the provisions of paragraph (k) of the AD, we will consider requests for approval of an AMOC
if sufficient data are submitted to substantiate that the change would provide an acceptable level of safety. We have not changed the AD in this regard.

Request To Revise Costs of Compliance

ATA on behalf of AA states that the Cost s of Compliance provided by the NPRM do not accurately reflect the true costs a ssociated with the proposed modifica tion. The commenters state that accomplishment of the minimum required servi ce bulletins would accrue approximately $800 per airplane in material for modification of the slid e in accordance with BFGoodrich Service Bulletin 25- 308, dated January 21, 2000, and $200 in labor for veri fication of incorporation of the new latch assembly.
We infer that the commenters would like us to revise the Costs of Co mpliance section of the NPRM. We disagree. We based our cost estimate of $516 per airplane for parts for the modification4 of the slide in accordance with BFGoodrich Service Bulletin 25-308, dated January 21, 2000, on
information from the manufacturer. The commenters di d not supply additional information to use as a basis for changing the Costs of Compliance section. Therefore, we do not find it necessary to change the AD in this regard.

Conclusion

We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting the AD as proposed.

Costs of Compliance

We estimate that this AD affects 480 airplanes of U.S. registry. We also estimate that it takes about 1 work-hour per product to comply with the in spection. The average labor rate is $80 per workhour. Based on these figures, we estimate the cost of this AD to U.S. operators to be $38,400 or $80 per product. The following table provides the estimated costs, at an average labor rate of $80 per work-hour, for U.S. operators to comply with th e concurrent actions, if applicable.

Estimated Concurrent Costs

Action Work
hours Parts Cost per airplane Fleet cost

Concurrent actions specified in Boeing Service
Bulletin 737-25-1404 2 $1,424 $1,584 Up to $760,320

Concurrent actions specified in Boeing Special
Attention Service Bulletin 737-25-1475 3 $1,740 $1,980 Up to $950,400

Concurrent actions specified in BFGoodrich
Service Bulletin 25-308 3 $516 $756 Up to $362,880

Authority for This Rulemaking

Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ''Subtitle VII: Aviation Programs,'' describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in ''Subtitle VII, Part A, Subpart III, Section 44701: General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safe ty in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action.

Regulatory Findings

This AD will not have federalism implications under Executive Order 13132. This AD will not
have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power a nd responsibilities among th e various levels of government. For the reasons discussed a bove, I certify that this AD:5 (1) Is not a ''significant regulatory action'' under Executive Order 12866, (2) Is not a ''significant rule'' under DOT Regulatory Policies and Pro cedures (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. You can find our regulatory evaluation and the es timated costs of compliance in the AD Docket.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safe ty, Incorporation by reference, Safety.

Adoption of the Amendment

Accordingly, under the authority delegated to me by the Administrator, the FAA amends 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. The FAA amends § 39.13 by adding the following new AD:6 

### FAA
Aircraft Certification Service 

## AIRWORTHINESS DIRECTIVE

www.faa.gov/aircraft/safety/alerts/ www.gpoaccess.gov/fr/advanced.html

2008-24-08 Boeing: Amendment 39-15748. Docket No. FAA- 2008-0176; Directorate Identifier
2007-NM-228-AD.

Effective Date

(a) This airworthiness directive (AD) is effective January 2, 2009.

Affected ADs

(b) None.

Applicability

(c) This AD applies to Boeing Model 737-600, -7 00, -700C, -800 and -900 series airplanes, certificated in any category, as identified in Boeing Service Bulletin 737-25-1491, dated April 23,
2007.

Unsafe Condition

(d) This AD results from reports that certain esca pe slides did not inflate when deployed or after the manual inflation cable was pulled. We are issuing this AD to prevent failure of an escape slide to inflate when deployed, which c ould result in the slide bei ng unusable during an emergency evacuation and consequent injury to passengers or crewmembers.

Compliance

(e) Comply with this AD within the compliance times specified, unless already done.

Inspection and Modification

(f) Within 36 months after the effective date of this AD, inspect the escape slides for the forward and aft entry and service doors to determine the Goodrich part number (P/N) and service bulletin number stenciled on the escape slide girts, and modi fy the escape slide assemblies, in accordance with the Accomplishment Instructions of Boei ng Service Bulletin 737-25-1491, dated April 23, 2007.

Note 1: Boeing Service Bulletin 737-25-1491, da ted April 23, 2007, refers to Goodrich Service Bulletin 25-338, Revision 1, dated March 31, 2004, as an additional source of service information for modifying the escape slide assemblies.

Concurrent Requirements

(g) Prior to or concurrently with accomplishing the actions requi red by paragraph (f) of this AD, do the applicable actions specified in paragrap hs (g)(1), (g)(2), and (g)(3) of this AD. (1) For Model 737-600, -700, and -800 series airp lanes identified in Boeing Service Bulletin 737-25-1404, dated May 25, 2000, equipped with any escape slide having P/N 5A3307-1, P/N 5A3307-3, P/N 5A3086-3, or P/N 5A3088-3: Modify the escape slide latch assembly in accordance7 with Boeing Service Bulletin 737-25-1404, date d May 25, 2000, as required by paragraph (a) of AD 2001-15-01; or Boeing Service Bulletin 737- 25-1404, Revision 1, dated April 18, 2002. (2) For Model 737-600, -700, -700C, -800 and -900 se ries airplanes equipped with any escape slide having P/N 5A3086-3 or P/N 5A3088-3: Inspect the four escape slides to determine the part
number and service bulletin number stenciled on th e escape slide girts, and replace the trigger housing on the regulator valve with an improved trigger housing if BFGood rich Service Bulletin 5A3086/5A3088-25-302 is not stenciled on the girt , in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 737-25-1475, dated November 26, 2002. For airplanes identified as Group 2 in Boeing Sp ecial Attention Service Bulletin 737-25-1475, dated November 26, 2002, a records review may be done in lieu of the inspection to determine the part
number.

Note 2: Boeing Special Attention Servi ce Bulletin 737-25-1475, dated November 26, 2002,
refers to Goodrich Service Bulletin 5A3086/5A 3088-25-336, dated June 17, 2002, as an additional source of service information for replacing the tr igger housing on the regula tor valve with a new, improved trigger housing.

(3) For Model 737-600, -700, -700C, -800 and -900 se ries airplanes equipped with any escape slide having P/N 5A3307-1, P/ N 5A3086-3, or P/N 5A3088-3; or P/N 5A3307-3 and BFGoodrich
Service Bulletin 5A3307-25-309 stenc iled on the girt: Replace the rod in the pilot valve regulator with a new, improved rod in accordance with BF Goodrich Service Bulletin 25-308, dated January 21,
2000.

Terminating Action for AD 2001-15-01

(h) For Model 737-600, -700, and -800 series airp lanes identified in Boeing Special Attention Service Bulletin 737-25-1403, dated May 4, 2000: A ccomplishing the replacement of the regulator piston plug in the vespel piston with a new piston plug, installati on of a new insolate pad on the valise, and removal of the trigger housing cover, in accordance with Goodrich Service Bulletin 25- 338, Revision 1, dated March 31, 2004, terminates th e modification specified in Boeing Special Attention Service Bulletin 737-25-1403, dated May 4, 2000, as required by paragraph (a) of AD 2001-15-01. All other appli cable actions required by paragraph (a) of AD 2001-15-01 must be fully complied with.

(i) For Model 737-600, -700, and -800 series airpla nes: Installation of a cover assembly on the trigger housing of the inflation cy linder on the escape slides in accordance with Boeing Special Attention Service Bulletin 737-25-1403, Revisi on 1, dated November 29, 2001, terminates the corresponding action required by paragraph (a) of AD 2001-15-01. A ll other applicable actions required by paragraph (a) of AD 2001- 15-01 must be fully complied with.

(j) For Model 737-600, -700, and -800 series airpla nes: Modification of th e escape slide latch assembly in accordance with Boeing Service Bu lletin 737-25-1404, Revision 1, dated April 18, 2002, terminates the corresponding action required by paragraph (a) of AD 2001-15-01. All other applicable actions required by paragraph (a) of AD 2001-15-01 must be fully complied with.

Alternative Methods of Compliance (AMOCs)

(k)(1) The Manager, Seattle Aircraft Certifi cation Office, FAA, ATTN: Robert K. Hettman, Aerospace Engineer, Cabin Safety and Envi ronmental Systems Branch, ANM-150S, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; te lephone (425) 917-6457, fax (425) 917-6590; has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR
39.19.8 (2) To request a different method of complian ce or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before usi ng any approved AMOC on any airplane to which the AMOC applies, notify your appropriate princi pal inspector (P I) in the FAA Flight Standards District Office (FSDO), or l acking a PI, your local FSDO.

Material Incorporated by Reference

(l) You must use the applicable service inform ation contained in Table 1 of this AD to do the actions required by this AD, unless the AD specifi es otherwise. If you accomplish the terminating actions for AD 2001-15-01 specified in this AD, you must use the applicable service information contained in Table 2 of this AD, unless the AD specifies otherwise.

Table 1 – Material incorporated by ref erence for actions required in this AD

Service Bulletin Revision Date

Boeing Service Bulletin 737-25-1404 Original May 25, 2000

Boeing Service Bulletin 737-25-1404 1 April 18, 2002

Boeing Service Bulletin 737-25- 1491 Original April 23, 2007

Boeing Special Attention Service Bullet in 737-25-1475 Original November 26, 2002

BFGoodrich Service Bulletin 25-308 Original January 21, 2000

Table 2 – Material incorporated by reference fo r the optional terminating action in this AD

Service Bulletin Revision Date

Boeing Service Bulletin 737-25-1404 1 April 18, 2002

Boeing Special Attention Service Bulletin 737-25-1403 1 November 29, 2001

Goodrich Service Bulletin 25-338 1 March 31, 2004

(1) The Director of the Federal Register appr oved the incorporation by re ference of the service
information listed in Table 3 of this AD under 5 U.S.C. 552(a) and 1 CFR part 51.

Table 3 – New material incorporated by reference

Service Bulletin Revision Date

Boeing Service Bulletin 737-25-1404 1 April 18, 2002

Boeing Service Bulletin 737-25- 1491 Original April 23, 2007

Boeing Special Attention Service Bullet in 737-25-1475 Original November 26, 2002

Goodrich Service Bulletin 25-308 Original January 21, 2000

(2) The Director of the Federal Register prev iously approved the incorporation by reference of Boeing Service Bulletin 737-25-1404, dated May 25, 2000, on August 28, 2001 (66 FR 38361, July 24, 2001). (3) For service information identified in this AD, contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207; telephone (206) 544-9990; fax ( 206) 766-5682; e-mail DDCS@boeing.com; Internet https://www.myboeingfleet.com.9 (4) You may review copies of the service inform ation that is incorporat ed by reference at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the National Archives and Records Administration (NARA) . For information on the availability of this material at NARA, call 202-741-60 30, or go to: http://www.archives.gov/federal_register/code_ of_federal_regulations/ibr_locations.html.

Issued in Renton, Washington, on November 16, 2008. Stephen P. Boyd, Assistant Manager, Transpor t Airplane Directorate,
Aircraft Certification Service.