Airworthiness Directives; McDonnell Douglas Model DC-9-10, -20, -30, -40 and -50 Series Airplanes, and Model DC-9-81 (MD-81), and DC-9-82 (MD-82) Airplanes, 13529-13533 [06-2409]

Download as PDF Federal Register / Vol. 71, No. 51 / Thursday, March 16, 2006 / Rules and Regulations 13529 TABLE 4.—SERVICE BULLETINS Cessna service bulletin— Dated— SB500–28–12 ................................................................................................................................................................. SBS550–28–08 ............................................................................................................................................................... SB550–28–14 ................................................................................................................................................................. SB550–28–15 ................................................................................................................................................................. SB560–28–10 ................................................................................................................................................................. SB560–28–11 ................................................................................................................................................................. June 14, 2004. May 7, 2004. December 2, 2003. January 20, 2004. April 23, 2004. March 12, 2004. TABLE 5.—TEMPORARY CHANGES Cessna temporary change— Dated— 500FM TC–R57–01 ............................................ 500FM TC–R57–02 ............................................ 500FM TC–R57–03 ............................................ 55BFM TC–R10–07 ........................................... 55BFM TC–R10–08 ........................................... 55BFM TC–R10–09 ........................................... 560FM TC–R13–01 ............................................ 560FM TC–R13–02 ............................................ 560FM TC–R13–03 ............................................ 56FMA TC–04–01 .............................................. 56FMA TC–04–02 .............................................. 56FMA TC–04–03 .............................................. 56FMB TC–R03–10 ........................................... 56FMB TC–R03–11 ........................................... 56FMB TC–R03–12 ........................................... S55CA TC–04–01 .............................................. S55CA TC–04–02 .............................................. S55CA TC–04–03 .............................................. S55FM TC–04–01 .............................................. S55FM TC–04–02 .............................................. S55FM TC–04–03 .............................................. April 5, 2004 ..................................................... April 5, 2004 ..................................................... April 5, 2004 ..................................................... March 17, 2004 ................................................ March 17, 2004 ................................................ March 17, 2004 ................................................ March 4, 2004 .................................................. March 4, 2004 .................................................. March 4, 2004 .................................................. March 4, 2004 .................................................. March 4, 2004 .................................................. March 4, 2004 .................................................. March 12, 2004 ................................................ March 12, 2004 ................................................ March 12, 2004 ................................................ July 8, 2004 ..................................................... July 8, 2004 ..................................................... July 8, 2004 ..................................................... March 4, 2004 .................................................. March 4, 2004 .................................................. March 4, 2004 .................................................. Issued in Renton, Washington, on March 3, 2006. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 06–2408 Filed 3–15–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–22121; Directorate Identifier 2004–NM–128–AD; Amendment 39–14512; AD 2006–06–04] RIN 2120–AA64 Airworthiness Directives; McDonnell Douglas Model DC–9–10, –20, –30, –40 and –50 Series Airplanes, and Model DC–9–81 (MD–81), and DC–9–82 (MD– 82) Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. HSROBINSON on PROD1PC70 with RULES AGENCY: SUMMARY: The FAA is superseding an existing airworthiness directive (AD), which applies to certain McDonnell VerDate Aug<31>2005 14:40 Mar 15, 2006 Jkt 208001 To the— Douglas Model DC–9–10, –20, –30, –40 and –50 series airplanes, and Model DC–9–81 (MD–81), and DC–9–82 (MD– 82) airplanes. That AD currently requires installing a water drain system for the slant pressure panels in the left and right wheel wells of the main landing gear (MLG). This new AD also requires inspecting the seal assemblies of the overwing emergency exit doors for defects and constant gap; replacing defective door seals; performing repetitive operational checks of the water drain system auto drain valve and corrective actions if necessary; and, for certain airplanes, modifying the insulation blankets on the slant pressure panels in the left and right MLG wheel wells. This AD results from reports of water runoff from the slant pressure panels in the left and right MLG wheel wells, which subsequently froze on the lateral control mixer and control cable assemblies. We are issuing this AD to prevent ice from forming on the lateral control mixer and control cable assemblies, which could reduce controllability of the airplane. DATES: This AD becomes effective April 20, 2006. The Director of the Federal Register approved the incorporation by reference PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 Cessna Cessna Cessna Cessna Cessna Cessna Cessna Cessna Cessna Cessna Cessna Cessna Cessna Cessna Cessna Cessna Cessna Cessna Cessna Cessna Cessna Model Model Model Model Model Model Model Model Model Model Model Model Model Model Model Model Model Model Model Model Model 500 AFM. 500 AFM. 500 AFM. 550 Citation Bravo AFM. 550 Citation Bravo AFM. 550 Citation Bravo AFM. 560 Citation V AFM. 560 Citation V AFM. 560 Citation V AFM. 560 Citation Ultra AFM. 560 Citation Ultra AFM. 560 Citation Ultra AFM. 560 AFM. 560 AFM. 560 AFM. S550 Citation S/II AFM. S550 Citation S/II AFM. S550 Citation S/II AFM. S550 Citation S/II AFM. S550 Citation S/II AFM. S550 Citation S/II AFM. of certain publications listed in the AD as of April 20, 2006. On August 18, 1993 (58 FR 38511, July 19, 1993), the Director of the Federal Register approved the incorporation by reference of certain other publications listed in the AD. You may examine the AD docket on the Internet at https:// dms.dot.gov or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., Nassif Building, room PL–401, Washington, DC. Contact Boeing Commercial Airplanes, Long Beach Division, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Data and Service Management, Dept. C1–L5A (D800–0024), for service information identified in this AD. ADDRESSES: FOR FURTHER INFORMATION CONTACT: Wahib Mina, Aerospace Engineer, Airframe Branch, ANM–120L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California 90712–4137; telephone (562) 627–5324; fax (562) 627–5210. SUPPLEMENTARY INFORMATION: E:\FR\FM\16MRR1.SGM 16MRR1 13530 Federal Register / Vol. 71, No. 51 / Thursday, March 16, 2006 / Rules and Regulations Examining the Docket You may examine the airworthiness directive (AD) docket on the Internet at https://dms.dot.gov or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the street address stated in the ADDRESSES section. Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that supersedes AD 93–13–07, amendment 39–8620 (58 FR 38511, July 19, 1993). The existing AD applies to certain McDonnell Douglas Model DC–9–10, –20, –30, –40 and –50 series airplanes, Model DC–9–81 and DC–9–82 series airplanes, and Model C–9 (Military) airplanes. That NPRM was published in the Federal Register on August 18, 2005 (70 FR 48502). That NPRM proposed to continue to require installing a water drain system for the slant pressure panels in the left and right wheel wells of the main landing gear (MLG). That NPRM also proposed to require inspecting the seal assemblies of the overwing emergency exit doors for defects and constant gap; replacing defective door seals; performing repetitive operational checks of the water drain system auto drain valve and corrective actions if necessary; and, for certain airplanes, modifying the insulation blankets on the slant pressure panels in the left and right MLG wheel wells. HSROBINSON on PROD1PC70 with RULES Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments that have been received on the NPRM. Request To Eliminate Need for Alternate Method of Compliance (AMOC) One commenter requests that we eliminate the need to request an AMOC. The commenter states that certain freighter airplanes had the auto drain valve removed in accordance with an AMOC with AD 93–13–07, which makes it impossible to perform the inspection required by paragraph (i) of the NPRM. The commenter states that revising paragraph (i) to address only airplanes that have not had the auto drain valve removed as discussed here would eliminate any need to request an AMOC in accordance with paragraph (i) of the NPRM. VerDate Aug<31>2005 14:40 Mar 15, 2006 Jkt 208001 We partially agree with this request. It is possible that an airplane that has had the auto drain valve removed as described could have the auto drain valve re-installed at some point. Therefore, we have revised paragraph (i) of the AD to be applicable to ‘‘any airplane which is equipped with an auto drain valve of the slant pressure panel water drain system.’’ Request To Provide Reference to Aircraft Maintenance Manual (AMM) One commenter requests that we provide a reference of where to obtain instructions to accomplish the operational check of the auto drain valve system. The commenter states that paragraph (i) of the NPRM does not contain any details of where to find such instructions. We agree with this request. Therefore, we have revised paragraph (i) of the AD to state that Chapter 51–10–01 of the Boeing MD–80 AMM or Chapter 51–00– 01 of the Douglas DC–9 AMM is one approved method of performing the operational check and replacement of the auto drain valve. Request To Revise Note 2 The same commenter requests that we revise Note 2 of the NPRM. The commenter states that paragraph (h) of the NPRM gives credit for inspections required by paragraph (g) of the AD that were performed before the effective date of the AD. The commenter believes that Note 2 should refer to paragraph (i) of the AD rather than paragraph (h) as Note 2 addresses documenting the repetitive inspections required by paragraph (i). We agree with this request. Note 2 of the AD incorrectly referred to paragraph (h) of the AD, and we have revised Note 2 to refer to paragraph (i) of the AD as discussed. Request To Eliminate Concurrent Service Bulletin The same commenter requests that we reconsider paragraph (j) of the NPRM. The commenter states that the modification of the insulation blankets installed on the slant pressure panel and the general visual inspection specified in McDonnell Douglas Service Bulletin DC9–53–268, dated August 11, 1995 are mandated by paragraphs (a)(1) and (a)(2) of AD 96–11–04, amendment 39–9629 (61 FR 25557, May 22, 1996). The commenter asserts that these actions are also specified in McDonnell Douglas Service Bulletin DC9–53–268 R01, Revision 01, dated July 18, 1996, which is mandated for concurrent accomplishment by this AD. The commenter also asserts that Service Bulletin DC9–53–268 R01, Revision 01 PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 states, ‘‘No additional work is required by this revision for aircraft modified by prior issue of this service bulletin.’’ We infer that the commenter believes that paragraph (j) is unnecessary and is requesting us to eliminate paragraph (j) from the AD. We partially agree with this request. Though the requirements of paragraph (a)(1) of AD 96–11–04 apply to all airplanes identified in the original issue of Service Bulletin DC9–53–268, dated August 11, 1995, the requirements of paragraph (j) of this AD apply only to certain airplanes identified in Service Bulletin DC9–53–268 R01, Revision 01, that are also identified in Boeing Service Bulletin DC9–53–179, Revision 2, dated May 27, 2004. Airplanes already modified as specified in Service Bulletin DC9–53–268 (the appropriate source of service information for doing the requirements of paragraph (a)(1) of AD 96–11–04), are in compliance with paragraph (j) of this AD. However, to prevent any confusion, we have revised paragraph (j) to clarify that only certain airplanes are subject to the requirements of paragraph (j). Request To Eliminate Inspection The same commenter requests that we eliminate the one-time visual inspection of the overwing door seal assemblies proposed by paragraph (g) of the NPRM. The commenter states that this inspection is required by paragraph (a)(2) of AD 96–11–04, in accordance with McDonnell Douglas Service Bulletin DC9–53–268, dated August 11, 1995. The commenter also states that Service Bulletin DC9–53–268 and Service Bulletin DC9–53–179, Revision 2, both state that this inspection is to be accomplished in accordance with Chapter 52–21–00 of the Boeing MD–80 AMM or Chapter 52–21–0 of the Douglas DC–9 AMM, as applicable. The commenter believes that the inspection requirements of paragraph (g) were previously addressed by AD 96–11–04 and should not be repeated here. We agree that both service bulletins refer to the same AMM chapter for performing the inspection required by paragraph (a)(2) of AD 96–11–04 and paragraph (g) of this AD. However, the inspection required by paragraph (g) of this AD is intended only for airplanes identified in the applicability of Service Bulletin DC9–53–179, Revision 2, and not for airplanes identified in the applicability of Service Bulletin DC9– 53–268. In addition, even if certain airplanes should be identified in both service bulletins, paragraph (e) of this AD states ‘‘unless the actions have already been done.’’ This statement means that, if any visual inspection of E:\FR\FM\16MRR1.SGM 16MRR1 Federal Register / Vol. 71, No. 51 / Thursday, March 16, 2006 / Rules and Regulations any overwing door seal assembly has been performed before the effective date of this AD in accordance with either service bulletin or paragraph (a)(2) of AD 96–11–04, no further visual inspection of that assembly is required by this AD. However, we have revised paragraph (h) of this AD to state that inspections done in accordance with paragraph (a)(2) of AD 96–11–04 are acceptable for compliance with the corresponding actions of this AD. Request To Supersede Additional AD One commenter requests that we revise the NPRM to supersede AD 96– 11–04 as well as AD 93–13–07. The commenter states that paragraphs (g) and (j) of this AD constitute the same inspections and modifications as those required by AD 96–11–04 to be accomplished in accordance with Service Bulletin DC9–53–268 or DC9– 53–268 R01, Revision 01. The commenter asserts that those inspections should be considered acceptable for compliance with the inspections required by paragraphs (g) and (j) of this AD. The commenter further asserts that the AMOC approved according to AD 96–11–04 should be approved as an AMOC for this AD. We partially agree with this request. As already discussed, the inspections required by paragraph (a)(2) of AD 96– 11–04 and paragraph (g) of this AD refer to the same AMM chapter; therefore, we have given credit for inspections done in accordance with paragraph (a)(2) of AD 96–11–04. Further, as already discussed and as specified in paragraph (j) of this AD, airplanes which have been modified in accordance with Service Bulletin DC9–53–268 as required by paragraph (a)(1) of AD 96– 11–04 require no additional modification. Therefore, we will not supersede AD 96–11–04. However, we agree that AMOCs approved according to AD 96–11–04 also are acceptable for compliance with the requirements of this AD. Therefore, we have revised paragraph (k)(2) of the NPRM to state that AMOCs previously approved according to AD 96–11–04 are approved as AMOCs for the corresponding requirements of this AD; and, due to clarification of the AMOC paragraph as discussed below, we have re-identified paragraph (k)(2) of the NPRM as paragraph (k)(3) of the AD. 13531 Clarification of AMOC Paragraph We have added new paragraph (k)(2) to this action to clarify the appropriate procedure for notifying the principal inspector before using any approved AMOC on any airplane to which the AMOC applies. Conclusion We have carefully reviewed the available data, including the comments that have been received, and determined that air safety and the public interest require adopting the AD with the changes described previously as well as certain minor editorial changes that do not affect the legal or technical content of the AD. We have determined that these changes will neither increase the economic burden on any operator nor increase the scope of the AD. Costs of Compliance There are about 2,025 airplanes of the affected design in the worldwide fleet. This AD affects about 1,131 airplanes of U.S. registry. The following table provides the estimated costs, using an average labor rate of $65 per hour, for U.S. operators to comply with this AD. ESTIMATED COSTS Work hours Action Install water drain system (required by AD 93–13–07) ........................................................... Inspect overwing emergency exit door seal assemblies (new action) .................................... Modify insulation blankets of slant pressure panel (new action for certain airplanes only) ... Check auto drain valve of slant pressure panel water drain system (new action) ................. 1 Per 8 1 8 1 Cost per airplane $613 N/A N/A N/A $1,133 65 520 165 Fleet cost $1,281,423 73,515 588,120 173,515 inspection cycle. Authority for This Rulemaking HSROBINSON on PROD1PC70 with RULES Parts Regulatory Findings 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 safety 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. We have determined that 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 and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866; (2) Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (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. We prepared a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. VerDate Aug<31>2005 14:40 Mar 15, 2006 Jkt 208001 PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 See the ADDRESSES section for a location to examine the regulatory evaluation. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, 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: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by removing amendment 39–8620 (58 FR 38511, July 19, 1993) and by adding I E:\FR\FM\16MRR1.SGM 16MRR1 13532 Federal Register / Vol. 71, No. 51 / Thursday, March 16, 2006 / Rules and Regulations the following new airworthiness directive (AD): only Boeing Service Bulletin DC9–53–179, Revision 2, dated May 27, 2004, may be used. 2006–06–04 McDonnell Douglas: Amendment 39–14512. Docket No. FAA–2005–22121; Directorate Identifier 2004–NM–128–AD. New Requirements of This AD Effective Date (a) This AD becomes effective April 20, 2006. Affected ADs (b) This AD supersedes AD 93–13–07. Applicability (c) This AD applies to McDonnell Douglas 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 (VC–9C), DC–9–32F, DC– 9–33F, DC–9–34, DC–9–34F, DC 9–32F (C– 9A, C–9B), DC–9–41, DC–9–51, DC–9–81 (MD–81), and DC–9–82 (MD–82) airplanes; as identified in Boeing Service Bulletin DC9– 53–179, Revision 2, dated May 27, 2004; certificated in any category. Unsafe Condition (d) This AD was prompted by reports of water runoff from the slant pressure panels in the left and right main landing gear (MLG) wheel wells, which subsequently froze on the lateral control mixer and control cable assemblies. We are issuing this AD to prevent ice from forming on the lateral control mixer and control cable assemblies, which could reduce controllability of the airplane. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Restatement of Requirements of AD 93–13– 07 Installation of Water Drain System (f) Within 24 months after August 18, 1993 (the effective date of AD 93–13–07), install a water drain system in the slant pressure panel, in accordance with McDonnell Douglas DC–9 Service Bulletin 53–179, dated January 18, 1985, as amended by Service Bulletin Change Notification 53–179 CN1, dated February 28, 1985, and Service Bulletin Change Notification 53–179 CN2, dated May 30, 1985; McDonnell Douglas Service Bulletin DC9–53–179, Revision 01, dated March 30, 1999; or Boeing Service Bulletin DC9–53–179, Revision 2, dated May 27, 2004. After the effective date of this AD, Inspection of Door Seal Assemblies (g) For all airplanes: Within 24 months after the effective date of this AD, perform a general visual inspection of the seal assemblies of the overwing emergency exit doors for defects and constant gap, and, before further flight, replace any defective door seal with a new door seal; in accordance with the Accomplishment Instructions of Boeing Service Bulletin DC9–53–179, Revision 2, dated May 27, 2004. Note 1: For the purposes of this AD, a general visual inspection is: ‘‘A visual examination of an interior or exterior area, installation, or assembly to detect obvious damage, failure, or irregularity. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to ensure visual access to all surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or droplight and may require removal or opening of access panels or doors. Stands, ladders, or platforms may be required to gain proximity to the area being checked.’’ Inspections Already Accomplished (h) Inspections accomplished before the effective date of this AD in accordance with McDonnell Douglas Service Bulletin DC9– 53–179, Revision 01, dated March 30, 1999; or McDonnell Douglas Service Bulletin DC9– 53–268, dated August 11, 1995, as referenced in paragraph (a)(2) of AD 96–11–04; are considered acceptable for compliance with the requirements of paragraph (g) of this AD. Operational Check of Drain Valve (i) For any airplane which is equipped with an auto drain valve of the slant pressure panel water drain system: Within 24 months after the effective date of this AD, perform an operational check of the auto drain valve and repeat this check at intervals not to exceed 24 months. If any auto drain valve is found to be obstructed or inoperative, before further flight, replace the auto drain valve with a new auto drain valve according to a method approved by the Manager, Los Angeles Aircraft Certification Office (ACO), FAA. Chapter 51–10–01 of the Boeing MD–80 Aircraft Maintenance Manual (AMM) or Chapter 51–00–01 of the Douglas DC–9 AMM, as applicable, is one approved method of performing the operational check and replacement of the auto drain valve. Note 2: After an operator complies with the requirements of paragraph (i) of this AD, paragraph (i) does not require that operators subsequently record accomplishment of those requirements each time an auto drain valve is checked or replaced according to that operator’s FAA-approved maintenance inspection program. Concurrent Service Bulletin for Certain Airplanes Only (j) For airplanes identified in Boeing Service Bulletin DC9–53–179, Revision 2, dated May 27, 2004, that are also identified in McDonnell Douglas Service Bulletin DC9– 53–268 R01, Revision 01, dated July 18, 1996: At the applicable compliance time specified in paragraph (j)(1) or (j)(2) of this AD, modify the insulation blankets on the slant pressure panels in the left and right wheel wells of the MLG, in accordance with Boeing Service Bulletin DC9–53–268 R01, Revision 01, dated July 18, 1996. Modifications accomplished before the effective date of this AD as specified in McDonnell Douglas Service Bulletin DC9–53–268, dated August 11, 1995, are acceptable for compliance with this paragraph. (1) For airplanes that have been modified, as specified in paragraph (f) of this AD, prior to the effective date of this AD: Within 24 months after the effective date of this AD. (2) For airplanes that have not been modified, as specified in paragraph (f) of this AD, prior to the effective date of this AD: Prior to or concurrently with the accomplishment of paragraph (f) of this AD. Alternative Methods of Compliance (AMOCs) (k)(1) The Manager, Los Angeles ACO, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with 14 CFR 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. (3) AMOCs approved previously in accordance with AD 93–13–07 and AD 96– 11–04 are approved as AMOCs for the corresponding requirements of this AD. Material Incorporated by Reference (l) You must use the service information listed in Table 1 of this AD, as applicable, to perform the actions that are required by this AD, unless the AD specifies otherwise. TABLE 1.—MATERIAL INCORPORATED BY REFERENCE HSROBINSON on PROD1PC70 with RULES Service information Revision level Boeing Service Bulletin DC9–53–179 ................................................................................. McDonnell Douglas DC–9 Service Bulletin 53–179 ........................................................... McDonnell Douglas Service Bulletin DC9–53–179 ............................................................ McDonnell Douglas Service Bulletin DC9–53–268 R01 ..................................................... Service Bulletin Change Notification 53–179 CN1 for McDonnell Douglas DC–9 Service Bulletin 53–179, dated January 18, 1985. Service Bulletin Change Notification 53–179 CN2 for McDonnell Douglas DC–9 Service Bulletin 53–179, dated January 18, 1985. 2 ........................................... Original ................................. 01 ......................................... 01 ......................................... Original ................................. May 27, 2004. January 18, 1985. March 30, 1999. July 18, 1996. February 28, 1985. Original ................................. May 30, 1985. VerDate Aug<31>2005 14:40 Mar 15, 2006 Jkt 208001 PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 E:\FR\FM\16MRR1.SGM 16MRR1 Date Federal Register / Vol. 71, No. 51 / Thursday, March 16, 2006 / Rules and Regulations (1) The Director of the Federal Register approved the incorporation by reference of McDonnell Douglas Service Bulletin DC9– 53–179, Revision 01, dated March 30, 1999; Boeing Service Bulletin DC9–53–179, Revision 2, dated May 27, 2004; and McDonnell Douglas Service Bulletin DC9– 53–268 R01, Revision 01, dated July 18, 1996; in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. (2) On August 18, 1993 (58 FR 38511, July 19, 1993), the Director of the Federal Register approved the incorporation by reference of McDonnell Douglas DC–9 Service Bulletin 53–179, dated January 18, 1985; and Service Bulletin Change Notification 53–179 CN1, dated February 28, 1985, and Service Bulletin Change Notification 53–179 CN2, dated May 30, 1985, for McDonnell Douglas DC–9 Service Bulletin 53–179, dated January 18, 1985. (3) Contact Boeing Commercial Airplanes, Long Beach Division, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Data and Service Management, Dept. C1–L5A (D800–0024), for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., room PL–401, Nassif Building, Washington, DC; on the Internet at https:// dms.dot.gov; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741–6030, or go to https://www.archives.gov/ federal_register/code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on March 3, 2006. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 06–2409 Filed 3–15–06; 8:45 am] BILLING CODE 4910–13–U DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–23648; Directorate Identifier 2006–CE–07–AD; Amendment 39– 14514; AD 2006–06–06] RIN 2120–AA64 Airworthiness Directives; The Cessna Aircraft Company Models 208 and 208B Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. HSROBINSON on PROD1PC70 with RULES AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) to supersede AD 2005–07–01, which applies to all The Cessna Aircraft Company (Cessna) Models 208 and 208B airplanes. AD 2005–07–01 VerDate Aug<31>2005 14:40 Mar 15, 2006 Jkt 208001 currently requires you to incorporate information into the applicable section of the Airplane Flight Manual (AFM). This AD is the result of several accidents/incidents with the affected airplanes during operations in icing conditions, FAA evaluation of Cessna flight test data, Cessna issuing AFM revisions, and FAA determining these revisions are necessary for safe operation. Consequently, this AD updates the actions of AD 2005–07–01 that require incorporation of text in the AFM and requires the insertion of new text in the AFM, and the fabrication and installation of placards. We are issuing this AD to assure that the pilot has enough information to prevent loss of control of the airplane while in-flight during icing conditions. DATES: This AD becomes effective on March 24, 2006. We must receive any comments on this AD by May 22, 2006. ADDRESSES: Use one of the following to submit comments on this AD: • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590– 001. • Fax: 1–202–493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. To get the service information identified in this proposed AD, contact The Cessna Aircraft Company, Product Support, P.O. Box 7706, Wichita, Kansas 67277–7706; telephone: (316) 517–5800; facsimile: (316) 942–9006. To view the comments to this AD, go to https://dms.dot.gov. The docket number is FAA–2006–23648; Directorate Identifier 2006–CE–07–AD. FOR FURTHER INFORMATION CONTACT: Robert P. Busto, Aerospace Engineer, Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Wichita, Kansas 67209; telephone: (316) 946– 4157; facsimile: (316) 946–4107. SUPPLEMENTARY INFORMATION: Has FAA taken any action to this point? Several accidents/incidents with Cessna Models 208 and 208B airplanes during operations in icing conditions, including six accidents in the 2003/ 2004 and 2004/2005 icing seasons, and PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 13533 nine events in the 2004/2005 icing season caused us to issue AD 2005–07– 01, Amendment 39–14025 (70 FR 15223, March 25, 2005). AD 2005–07–01 currently requires you to incorporate information into the applicable section of the Airplane Flight Manual (AFM) on Cessna Models 208 and 208B. This accident/incident data and the evaluation of recent Cessna flight test data prompted us to issue AD 2006–01– 11, Amendment 39–14450 (71 FR 1941). AD 2006–01–11 requires the installation of a pilot assist handle, pneumatic deicing boots on the cargo pod and landing gear struts, and changes to the Limitations section of AFM if the airplane is to be operated in ground icing conditions and approved for flight into known or forecast icing conditions. What has happened since AD 2005– 07–01 to initiate this AD action? So far for the icing season of 2005/2006, the FAA is aware of the following: • On October 6, 2005, a fatal accident occurred shortly after takeoff in which the pilot reported a failure to maintain altitude while in icing conditions and a subsequent loss of control. • On November 19, 2005, a Model C208 experienced a loss of controlled flight while in icing conditions during descent that resulted in a fatal accident. • On November 22, 2005, an incident occurred in which a Model C208 suffered a loss of control during climb with the autopilot engaged in icing conditions. • On December 5, 2005, Cessna published revisions to the AFM Icing Supplement. These revisions incorporated climb performance data in icing based on a natural icing encounter in moderate, mixed conditions. • Cessna briefed the FAA that flight testing with ice shapes representing intercycle ice in a moderate, clear ice encounter showed the actual climb performance is lower than the data published in the AFM Icing Supplement revision, dated December 5, 2005, and that the aural stall warning system will not activate prior to stall in some icing conditions. • The AFM Icing Supplement, dated December 5, 2005, contained incorrect maximum weight limits for the 600 HP versions of the Model 208. In summary, for the nine events that occurred during the 2004/2005 icing season, airplane performance was degraded to a point in which altitude could not be maintained or the airplane could not climb to exit icing conditions. In one accident and one incident this 2005/2006 icing season, inadequate situational awareness may have contributed to a loss of controlled flight E:\FR\FM\16MRR1.SGM 16MRR1

Agencies

[Federal Register Volume 71, Number 51 (Thursday, March 16, 2006)]
[Rules and Regulations]
[Pages 13529-13533]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-2409]

-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-22121; Directorate Identifier 2004-NM-128-AD;
Amendment 39-14512; AD 2006-06-04]
RIN 2120-AA64

Airworthiness Directives; McDonnell Douglas Model DC-9-10, -20, -
30, -40 and -50 Series Airplanes, and Model DC-9-81 (MD-81), and DC-9-
82 (MD-82) Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: The FAA is superseding an existing airworthiness directive
(AD), which applies to certain McDonnell Douglas Model DC-9-10, -20, -
30, -40 and -50 series airplanes, and Model DC-9-81 (MD-81), and DC-9-
82 (MD-82) airplanes. That AD currently requires installing a water
drain system for the slant pressure panels in the left and right wheel
wells of the main landing gear (MLG). This new AD also requires
inspecting the seal assemblies of the overwing emergency exit doors for
defects and constant gap; replacing defective door seals; performing
repetitive operational checks of the water drain system auto drain
valve and corrective actions if necessary; and, for certain airplanes,
modifying the insulation blankets on the slant pressure panels in the
left and right MLG wheel wells. This AD results from reports of water
runoff from the slant pressure panels in the left and right MLG wheel
wells, which subsequently froze on the lateral control mixer and
control cable assemblies. We are issuing this AD to prevent ice from
forming on the lateral control mixer and control cable assemblies,
which could reduce controllability of the airplane.

DATES: This AD becomes effective April 20, 2006.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of April 20,
2006.
On August 18, 1993 (58 FR 38511, July 19, 1993), the Director of
the Federal Register approved the incorporation by reference of certain
other publications listed in the AD.

ADDRESSES: You may examine the AD docket on the Internet at https://
dms.dot.gov or in person at the Docket Management Facility, U.S.
Department of Transportation, 400 Seventh Street SW., Nassif Building,
room PL-401, Washington, DC.
Contact Boeing Commercial Airplanes, Long Beach Division, 3855
Lakewood Boulevard, Long Beach, California 90846, Attention: Data and
Service Management, Dept. C1-L5A (D800-0024), for service information
identified in this AD.

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

SUPPLEMENTARY INFORMATION:

[[Page 13530]]

Examining the Docket

You may examine the airworthiness directive (AD) docket on the
Internet at https://dms.dot.gov or in person at the Docket Management
Facility office between 9 a.m. and 5 p.m., Monday through Friday,
except Federal holidays. The Docket Management Facility office
(telephone (800) 647-5227) is located on the plaza level of the Nassif
Building at the street address stated in the ADDRESSES section.

Discussion

The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to include an AD that supersedes AD 93-13-07, amendment 39-
8620 (58 FR 38511, July 19, 1993). The existing AD applies to certain
McDonnell Douglas Model DC-9-10, -20, -30, -40 and -50 series
airplanes, Model DC-9-81 and DC-9-82 series airplanes, and Model C-9
(Military) airplanes. That NPRM was published in the Federal Register
on August 18, 2005 (70 FR 48502). That NPRM proposed to continue to
require installing a water drain system for the slant pressure panels
in the left and right wheel wells of the main landing gear (MLG). That
NPRM also proposed to require inspecting the seal assemblies of the
overwing emergency exit doors for defects and constant gap; replacing
defective door seals; performing repetitive operational checks of the
water drain system auto drain valve and corrective actions if
necessary; and, for certain airplanes, modifying the insulation
blankets on the slant pressure panels in the left and right MLG wheel
wells.

Comments

We provided the public the opportunity to participate in the
development of this AD. We have considered the comments that have been
received on the NPRM.

Request To Eliminate Need for Alternate Method of Compliance (AMOC)

One commenter requests that we eliminate the need to request an
AMOC. The commenter states that certain freighter airplanes had the
auto drain valve removed in accordance with an AMOC with AD 93-13-07,
which makes it impossible to perform the inspection required by
paragraph (i) of the NPRM. The commenter states that revising paragraph
(i) to address only airplanes that have not had the auto drain valve
removed as discussed here would eliminate any need to request an AMOC
in accordance with paragraph (i) of the NPRM.
We partially agree with this request. It is possible that an
airplane that has had the auto drain valve removed as described could
have the auto drain valve re-installed at some point. Therefore, we
have revised paragraph (i) of the AD to be applicable to ``any airplane
which is equipped with an auto drain valve of the slant pressure panel
water drain system.''

Request To Provide Reference to Aircraft Maintenance Manual (AMM)

One commenter requests that we provide a reference of where to
obtain instructions to accomplish the operational check of the auto
drain valve system. The commenter states that paragraph (i) of the NPRM
does not contain any details of where to find such instructions.
We agree with this request. Therefore, we have revised paragraph
(i) of the AD to state that Chapter 51-10-01 of the Boeing MD-80 AMM or
Chapter 51-00-01 of the Douglas DC-9 AMM is one approved method of
performing the operational check and replacement of the auto drain
valve.

Request To Revise Note 2

The same commenter requests that we revise Note 2 of the NPRM. The
commenter states that paragraph (h) of the NPRM gives credit for
inspections required by paragraph (g) of the AD that were performed
before the effective date of the AD. The commenter believes that Note 2
should refer to paragraph (i) of the AD rather than paragraph (h) as
Note 2 addresses documenting the repetitive inspections required by
paragraph (i).
We agree with this request. Note 2 of the AD incorrectly referred
to paragraph (h) of the AD, and we have revised Note 2 to refer to
paragraph (i) of the AD as discussed.

Request To Eliminate Concurrent Service Bulletin

The same commenter requests that we reconsider paragraph (j) of the
NPRM. The commenter states that the modification of the insulation
blankets installed on the slant pressure panel and the general visual
inspection specified in McDonnell Douglas Service Bulletin DC9-53-268,
dated August 11, 1995 are mandated by paragraphs (a)(1) and (a)(2) of
AD 96-11-04, amendment 39-9629 (61 FR 25557, May 22, 1996). The
commenter asserts that these actions are also specified in McDonnell
Douglas Service Bulletin DC9-53-268 R01, Revision 01, dated July 18,
1996, which is mandated for concurrent accomplishment by this AD. The
commenter also asserts that Service Bulletin DC9-53-268 R01, Revision
01 states, ``No additional work is required by this revision for
aircraft modified by prior issue of this service bulletin.'' We infer
that the commenter believes that paragraph (j) is unnecessary and is
requesting us to eliminate paragraph (j) from the AD.
We partially agree with this request. Though the requirements of
paragraph (a)(1) of AD 96-11-04 apply to all airplanes identified in
the original issue of Service Bulletin DC9-53-268, dated August 11,
1995, the requirements of paragraph (j) of this AD apply only to
certain airplanes identified in Service Bulletin DC9-53-268 R01,
Revision 01, that are also identified in Boeing Service Bulletin DC9-
53-179, Revision 2, dated May 27, 2004. Airplanes already modified as
specified in Service Bulletin DC9-53-268 (the appropriate source of
service information for doing the requirements of paragraph (a)(1) of
AD 96-11-04), are in compliance with paragraph (j) of this AD. However,
to prevent any confusion, we have revised paragraph (j) to clarify that
only certain airplanes are subject to the requirements of paragraph
(j).

Request To Eliminate Inspection

The same commenter requests that we eliminate the one-time visual
inspection of the overwing door seal assemblies proposed by paragraph
(g) of the NPRM. The commenter states that this inspection is required
by paragraph (a)(2) of AD 96-11-04, in accordance with McDonnell
Douglas Service Bulletin DC9-53-268, dated August 11, 1995. The
commenter also states that Service Bulletin DC9-53-268 and Service
Bulletin DC9-53-179, Revision 2, both state that this inspection is to
be accomplished in accordance with Chapter 52-21-00 of the Boeing MD-80
AMM or Chapter 52-21-0 of the Douglas DC-9 AMM, as applicable. The
commenter believes that the inspection requirements of paragraph (g)
were previously addressed by AD 96-11-04 and should not be repeated
here.
We agree that both service bulletins refer to the same AMM chapter
for performing the inspection required by paragraph (a)(2) of AD 96-11-
04 and paragraph (g) of this AD. However, the inspection required by
paragraph (g) of this AD is intended only for airplanes identified in
the applicability of Service Bulletin DC9-53-179, Revision 2, and not
for airplanes identified in the applicability of Service Bulletin DC9-
53-268. In addition, even if certain airplanes should be identified in
both service bulletins, paragraph (e) of this AD states ``unless the
actions have already been done.'' This statement means that, if any
visual inspection of

[[Page 13531]]

any overwing door seal assembly has been performed before the effective
date of this AD in accordance with either service bulletin or paragraph
(a)(2) of AD 96-11-04, no further visual inspection of that assembly is
required by this AD. However, we have revised paragraph (h) of this AD
to state that inspections done in accordance with paragraph (a)(2) of
AD 96-11-04 are acceptable for compliance with the corresponding
actions of this AD.

Request To Supersede Additional AD

One commenter requests that we revise the NPRM to supersede AD 96-
11-04 as well as AD 93-13-07. The commenter states that paragraphs (g)
and (j) of this AD constitute the same inspections and modifications as
those required by AD 96-11-04 to be accomplished in accordance with
Service Bulletin DC9-53-268 or DC9-53-268 R01, Revision 01. The
commenter asserts that those inspections should be considered
acceptable for compliance with the inspections required by paragraphs
(g) and (j) of this AD. The commenter further asserts that the AMOC
approved according to AD 96-11-04 should be approved as an AMOC for
this AD.
We partially agree with this request. As already discussed, the
inspections required by paragraph (a)(2) of AD 96-11-04 and paragraph
(g) of this AD refer to the same AMM chapter; therefore, we have given
credit for inspections done in accordance with paragraph (a)(2) of AD
96-11-04. Further, as already discussed and as specified in paragraph
(j) of this AD, airplanes which have been modified in accordance with
Service Bulletin DC9-53-268 as required by paragraph (a)(1) of AD 96-
11-04 require no additional modification. Therefore, we will not
supersede AD 96-11-04. However, we agree that AMOCs approved according
to AD 96-11-04 also are acceptable for compliance with the requirements
of this AD. Therefore, we have revised paragraph (k)(2) of the NPRM to
state that AMOCs previously approved according to AD 96-11-04 are
approved as AMOCs for the corresponding requirements of this AD; and,
due to clarification of the AMOC paragraph as discussed below, we have
re-identified paragraph (k)(2) of the NPRM as paragraph (k)(3) of the
AD.

Clarification of AMOC Paragraph

We have added new paragraph (k)(2) to this action to clarify the
appropriate procedure for notifying the principal inspector before
using any approved AMOC on any airplane to which the AMOC applies.

Conclusion

We have carefully reviewed the available data, including the
comments that have been received, and determined that air safety and
the public interest require adopting the AD with the changes described
previously as well as certain minor editorial changes that do not
affect the legal or technical content of the AD. We have determined
that these changes will neither increase the economic burden on any
operator nor increase the scope of the AD.

Costs of Compliance

There are about 2,025 airplanes of the affected design in the
worldwide fleet. This AD affects about 1,131 airplanes of U.S.
registry. The following table provides the estimated costs, using an
average labor rate of $65 per hour, for U.S. operators to comply with
this AD.

Estimated Costs
----------------------------------------------------------------------------------------------------------------
Work Cost per
Action hours Parts airplane Fleet cost
----------------------------------------------------------------------------------------------------------------
Install water drain system (required by AD 93-13-07).......... 8 $613 $1,133 $1,281,423
Inspect overwing emergency exit door seal assemblies (new 1 N/A 65 73,515
action)......................................................
Modify insulation blankets of slant pressure panel (new action 8 N/A 520 588,120
for certain airplanes only)..................................
Check auto drain valve of slant pressure panel water drain 1 N/A \1\65 \1\73,515
system (new action)..........................................
----------------------------------------------------------------------------------------------------------------
\1\ Per inspection cycle.

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 safety 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

We have determined that 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
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (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.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket. See the ADDRESSES
section for a location to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing amendment 39-8620 (58 FR 38511, July 19, 1993) and by adding

[[Page 13532]]

the following new airworthiness directive (AD):

2006-06-04 McDonnell Douglas: Amendment 39-14512. Docket No. FAA-
2005-22121; Directorate Identifier 2004-NM-128-AD.

Effective Date

(a) This AD becomes effective April 20, 2006.

Affected ADs

(b) This AD supersedes AD 93-13-07.

Applicability

(c) This AD applies to McDonnell Douglas 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 (VC-9C), DC-9-32F, DC-9-33F, DC-9-34, DC-9-34F, DC 9-32F (C-9A,
C-9B), DC-9-41, DC-9-51, DC-9-81 (MD-81), and DC-9-82 (MD-82)
airplanes; as identified in Boeing Service Bulletin DC9-53-179,
Revision 2, dated May 27, 2004; certificated in any category.

Unsafe Condition

(d) This AD was prompted by reports of water runoff from the
slant pressure panels in the left and right main landing gear (MLG)
wheel wells, which subsequently froze on the lateral control mixer
and control cable assemblies. We are issuing this AD to prevent ice
from forming on the lateral control mixer and control cable
assemblies, which could reduce controllability of the airplane.

Compliance

(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.

Restatement of Requirements of AD 93-13-07

Installation of Water Drain System

(f) Within 24 months after August 18, 1993 (the effective date
of AD 93-13-07), install a water drain system in the slant pressure
panel, in accordance with McDonnell Douglas DC-9 Service Bulletin
53-179, dated January 18, 1985, as amended by Service Bulletin
Change Notification 53-179 CN1, dated February 28, 1985, and Service
Bulletin Change Notification 53-179 CN2, dated May 30, 1985;
McDonnell Douglas Service Bulletin DC9-53-179, Revision 01, dated
March 30, 1999; or Boeing Service Bulletin DC9-53-179, Revision 2,
dated May 27, 2004. After the effective date of this AD, only Boeing
Service Bulletin DC9-53-179, Revision 2, dated May 27, 2004, may be
used.

New Requirements of This AD

Inspection of Door Seal Assemblies

(g) For all airplanes: Within 24 months after the effective date
of this AD, perform a general visual inspection of the seal
assemblies of the overwing emergency exit doors for defects and
constant gap, and, before further flight, replace any defective door
seal with a new door seal; in accordance with the Accomplishment
Instructions of Boeing Service Bulletin DC9-53-179, Revision 2,
dated May 27, 2004.

Note 1: For the purposes of this AD, a general visual inspection
is: ``A visual examination of an interior or exterior area,
installation, or assembly to detect obvious damage, failure, or
irregularity. This level of inspection is made from within touching
distance unless otherwise specified. A mirror may be necessary to
ensure visual access to all surfaces in the inspection area. This
level of inspection is made under normally available lighting
conditions such as daylight, hangar lighting, flashlight, or
droplight and may require removal or opening of access panels or
doors. Stands, ladders, or platforms may be required to gain
proximity to the area being checked.''

Inspections Already Accomplished

(h) Inspections accomplished before the effective date of this
AD in accordance with McDonnell Douglas Service Bulletin DC9-53-179,
Revision 01, dated March 30, 1999; or McDonnell Douglas Service
Bulletin DC9-53-268, dated August 11, 1995, as referenced in
paragraph (a)(2) of AD 96-11-04; are considered acceptable for
compliance with the requirements of paragraph (g) of this AD.

Operational Check of Drain Valve

(i) For any airplane which is equipped with an auto drain valve
of the slant pressure panel water drain system: Within 24 months
after the effective date of this AD, perform an operational check of
the auto drain valve and repeat this check at intervals not to
exceed 24 months. If any auto drain valve is found to be obstructed
or inoperative, before further flight, replace the auto drain valve
with a new auto drain valve according to a method approved by the
Manager, Los Angeles Aircraft Certification Office (ACO), FAA.
Chapter 51-10-01 of the Boeing MD-80 Aircraft Maintenance Manual
(AMM) or Chapter 51-00-01 of the Douglas DC-9 AMM, as applicable, is
one approved method of performing the operational check and
replacement of the auto drain valve.

Note 2: After an operator complies with the requirements of
paragraph (i) of this AD, paragraph (i) does not require that
operators subsequently record accomplishment of those requirements
each time an auto drain valve is checked or replaced according to
that operator's FAA-approved maintenance inspection program.

Concurrent Service Bulletin for Certain Airplanes Only

(j) For airplanes identified in Boeing Service Bulletin DC9-53-
179, Revision 2, dated May 27, 2004, that are also identified in
McDonnell Douglas Service Bulletin DC9-53-268 R01, Revision 01,
dated July 18, 1996: At the applicable compliance time specified in
paragraph (j)(1) or (j)(2) of this AD, modify the insulation
blankets on the slant pressure panels in the left and right wheel
wells of the MLG, in accordance with Boeing Service Bulletin DC9-53-
268 R01, Revision 01, dated July 18, 1996. Modifications
accomplished before the effective date of this AD as specified in
McDonnell Douglas Service Bulletin DC9-53-268, dated August 11,
1995, are acceptable for compliance with this paragraph.
(1) For airplanes that have been modified, as specified in
paragraph (f) of this AD, prior to the effective date of this AD:
Within 24 months after the effective date of this AD.
(2) For airplanes that have not been modified, as specified in
paragraph (f) of this AD, prior to the effective date of this AD:
Prior to or concurrently with the accomplishment of paragraph (f) of
this AD.

Alternative Methods of Compliance (AMOCs)

(k)(1) The Manager, Los Angeles ACO, has the authority to
approve AMOCs for this AD, if requested in accordance with the
procedures found in 14 CFR 39.19.
(2) Before using any AMOC approved in accordance with 14 CFR
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
Certificate Holding District Office.
(3) AMOCs approved previously in accordance with AD 93-13-07 and
AD 96-11-04 are approved as AMOCs for the corresponding requirements
of this AD.

Material Incorporated by Reference

(l) You must use the service information listed in Table 1 of
this AD, as applicable, to perform the actions that are required by
this AD, unless the AD specifies otherwise.

Table 1.--Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Service information Revision level Date
----------------------------------------------------------------------------------------------------------------
Boeing Service Bulletin DC9-53-179........ 2.......................... May 27, 2004.
McDonnell Douglas DC-9 Service Bulletin 53- Original................... January 18, 1985.
179.
McDonnell Douglas Service Bulletin DC9-53- 01......................... March 30, 1999.
179.
McDonnell Douglas Service Bulletin DC9-53- 01......................... July 18, 1996.
268 R01.
Service Bulletin Change Notification 53- Original................... February 28, 1985.
179 CN1 for McDonnell Douglas DC-9
Service Bulletin 53-179, dated January
18, 1985.
Service Bulletin Change Notification 53- Original................... May 30, 1985.
179 CN2 for McDonnell Douglas DC-9
Service Bulletin 53-179, dated January
18, 1985.
----------------------------------------------------------------------------------------------------------------

[[Page 13533]]

(1) The Director of the Federal Register approved the
incorporation by reference of McDonnell Douglas Service Bulletin
DC9-53-179, Revision 01, dated March 30, 1999; Boeing Service
Bulletin DC9-53-179, Revision 2, dated May 27, 2004; and McDonnell
Douglas Service Bulletin DC9-53-268 R01, Revision 01, dated July 18,
1996; in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
(2) On August 18, 1993 (58 FR 38511, July 19, 1993), the
Director of the Federal Register approved the incorporation by
reference of McDonnell Douglas DC-9 Service Bulletin 53-179, dated
January 18, 1985; and Service Bulletin Change Notification 53-179
CN1, dated February 28, 1985, and Service Bulletin Change
Notification 53-179 CN2, dated May 30, 1985, for McDonnell Douglas
DC-9 Service Bulletin 53-179, dated January 18, 1985.
(3) Contact Boeing Commercial Airplanes, Long Beach Division,
3855 Lakewood Boulevard, Long Beach, California 90846, Attention:
Data and Service Management, Dept. C1-L5A (D800-0024), for a copy of
this service information. You may review copies at the Docket
Management Facility, U.S. Department of Transportation, 400 Seventh
Street SW., room PL-401, Nassif Building, Washington, DC; on the
Internet at https://dms.dot.gov; or at the National Archives and
Records Administration (NARA). For information on the availability
of this material at the NARA, call (202) 741-6030, or go to https://
www.archives.gov/federal_register/code_of_federal_regulations/
ibr_locations.html.

Issued in Renton, Washington, on March 3, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 06-2409 Filed 3-15-06; 8:45 am]
BILLING CODE 4910-13-U

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