Airworthiness Directives; Boeing Model 737-100, -200, and -200C Series Airplanes, 40391-40394 [06-6152]

Download as PDF Federal Register / Vol. 71, No. 136 / Monday, July 17, 2006 / Rules and Regulations 40391 Actions Compliance Procedures Verify that the current flight idle blade angles are set at 12 degrees. If not already set to 12 degrees, set the flight idle blade angles to 12 degrees. Within the next 100 hours time-in-service after August 21, 2006 (the effective date of this AD). Follow Mitsubishi Aircraft International, Inc. Service Bulletin No. SB016/61–001, dated March 18, 1980. Alternative Methods of Compliance (AMOCs) DEPARTMENT OF TRANSPORTATION (f) The Manager, Forth Worth Aircraft Certification Office (ACO), FAA, ATTN: Rao Edupuganti, Aerospace Engineer, Fort Worth ACO, ASW–150, Rotorcraft Directorate, FAA, 2601 Meacham Boulevard, Fort Worth, Texas 76137–4298; telephone: 817–222–5284; facsimile: 817–222–5960, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Federal Aviation Administration Material Incorporated by Reference (g) You must do the actions required by this AD following the instructions in Mitsubishi Aircraft International, Inc. Service Bulletin No. SB016/61–001, dated March 18, 1980. The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get a copy of this service information, contact Mitsubishi Heavy Industries, Ltd., 4951 Airport Parkway, Suite 800, Addison, Texas 75001 telephone: 972–934–5480; facsimile: 972–934–5488. To review copies of this service information, go to the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, go to: http:// www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html or call (202) 741–6030. To view the AD docket, go to the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590–001 or on the Internet at http:// dms.dot.gov. The docket number is FAA– 2006–23644; Directorate Identifier 2006–CE– 03–AD. Issued in Kansas City, Missouri, on July 5, 2006. Kim Smith, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 06–6179 Filed 7–14–06; 8:45 am] rmajette on PROD1PC67 with RULES BILLING CODE 4910–13–P VerDate Aug<31>2005 15:22 Jul 14, 2006 Jkt 208001 14 CFR Part 39 [Docket No. FAA–2006–24432; Directorate Identifier 2005–NM–227–AD; Amendment 39–14678; AD 2006–14–07] RIN 2120–AA64 Airworthiness Directives; Boeing Model 737–100, –200, and –200C Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 737 series airplanes. That AD currently requires inspection of the elevator tab inboard hinge support structure to detect fatigue cracking and corrective action if necessary. That AD also provides an optional terminating action. This new AD adds airplanes to the applicability and requires new repetitive inspections. For airplanes having elevators with laminated rear spars, this new AD requires repetitive inspections for interlaminar corrosion, delamination, or disbonding in the rear spar, repetitive inspections for cracking in the spar web, and repair including related investigative/corrective actions if necessary. For airplanes having elevators with solid rear spars, this new AD requires repetitive inspections for cracking in the spar web and repair including related investigative/ corrective actions if necessary. This AD results from reports of cracks in the elevator rear spar web at the tab hinge bracket locations. We are issuing this AD to detect and correct cracking, corrosion, interlaminar corrosion, delamination, and disbonding in the elevator rear spar, which may reduce elevator stiffness and lead to in-flight vibration. In-flight vibration may lead to elevator and horizontal stabilizer damage and reduced controllability of the airplane. DATES: This AD becomes effective August 21, 2006. The Director of the Federal Register approved the incorporation by reference PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 of certain publications listed in the AD as of August 21, 2006. ADDRESSES: You may examine the AD docket on the Internet at http:// 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, P.O. Box 3707, Seattle, Washington 98124–2207, for service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Nancy Marsh, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6440; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: Examining the Docket You may examine the airworthiness directive (AD) docket on the Internet at http://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 76–11–05 R1, amendment 39–6234 (54 FR 25709, June 19, 1989). The existing AD applies to certain Boeing Model 737 series airplanes. That NPRM was published in the Federal Register on April 13, 2006 (71 FR 19144). That NPRM proposed to continue to require inspection of the elevator tab inboard hinge support structure to detect fatigue cracking and corrective action if necessary. That NPRM also proposed to continue to provide an optional terminating action for the existing inspections. That NPRM proposed to add airplanes to the applicability and to require new repetitive inspections. For airplanes having elevators with laminated rear spars, that NPRM proposed to require repetitive inspections for interlaminar corrosion, delamination, or disbonding E:\FR\FM\17JYR1.SGM 17JYR1 40392 Federal Register / Vol. 71, No. 136 / Monday, July 17, 2006 / Rules and Regulations in the rear spar, repetitive inspections for cracking in the spar web, and repair including related investigative/ corrective actions if necessary. For airplanes having elevators with solid rear spars, that NPRM proposed to require repetitive inspections for cracking in the spar web and repair including related investigative/ corrective actions if necessary. Comments We provided the public the opportunity to participate in the development of this AD. No comments have been received on the NPRM or on the determination of the cost to the public. Conclusion We have carefully reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed. Costs of Compliance There are about 1,355 airplanes of the affected design in the worldwide fleet. The following table provides the estimated costs for U.S. operators to comply with this AD. ESTIMATED COSTS Action Inspection, per inspection cycle Average labor rate per hour Work hours 10–100 rmajette on PROD1PC67 with RULES 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. VerDate Aug<31>2005 15:22 Jul 14, 2006 Jkt 208001 Cost per airplane $80 $800–$8,000, cycle. per inspection 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 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 39–6234 (54 FR 25709, June 19, 1989) and by adding the following new airworthiness directive (AD): I 2006–14–07 Boeing: Amendment 39–14678. Docket No. FAA–2006–24432; Directorate Identifier 2005–NM–227–AD. Effective Date (a) This AD becomes effective August 21, 2006. Affected ADs (b) This AD supersedes AD 76–11–05 R1. Applicability (c) This AD applies to Boeing Model 737– 100, –200, and –200C series airplanes, certificated in any category; as identified in Boeing Alert Service Bulletin 737–55A1078, dated October 27, 2005. PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 Number of U.S.-registered airplanes 230 Fleet cost $184,000–$1,840,000, per inspection cycle. Unsafe Condition (d) This AD results from reports of cracks in the elevator rear spar web at the tab hinge bracket locations. We are issuing this AD to detect and correct cracking, corrosion, interlaminar corrosion, delamination, and disbonding in the elevator rear spar, which may reduce elevator stiffness and lead to inflight vibration. In-flight vibration may lead to elevator and horizontal stabilizer damage and reduced 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 Certain Requirements of AD 76–11–05 R1 (f) For Model 737–100, –200, and –200C series airplanes, line number 001 through 491 inclusive: Within the next 300 hours time-in-service after July 24, 1989 (the effective date of AD 76–11–05 R1), unless accomplished within the last 700 hours timein-service, and at intervals thereafter not to exceed 1,000 hours time-in-service, conduct the inspection required by paragraph (g) of this AD. Accomplishing the initial inspections specified in paragraph (j) of this AD terminates the requirements of this paragraph. (g) For Model 737–100, –200, and –200C series airplanes, line number 001 through 491 inclusive: At the times specified in paragraph (f) of this AD, inspect for excessive deflection of the elevator tab, right and left hand, in accordance with the inspection procedures specified in Section III, Part I, paragraphs C. and D., of Boeing Alert Service Bulletin 737–55–A1020, Revision 1, dated August 20, 1976; Revision 2, dated February 11, 1977; or 737–55A1020, Revision 3, dated December 22, 1988. If the elevator tab-toelevator relative deflection exceeds 1/10 inch, prior to further flight, modify the elevator in accordance with paragraph (h) of this AD. Accomplishing the initial inspections specified in paragraph (j) of this AD terminates the requirements of this paragraph. E:\FR\FM\17JYR1.SGM 17JYR1 40393 Federal Register / Vol. 71, No. 136 / Monday, July 17, 2006 / Rules and Regulations (h) For Model 737–100, –200, and –200C series airplanes, line number 001 through 491 inclusive: Installation of one of the modifications specified in Boeing Alert Service Bulletin 737–55–A1020, Revision 1, dated August 20, 1976; 737–55–A1020, Revision 2, dated February 11, 1977; or 737– 55A1020, Revision 3, dated December 22, 1988; Section III, Part II, including installation of the bolt retainer clips or the preventive modification specified in Boeing Service Bulletin 737–55–1022, Section III, Part II, dated April 15, 1977; is considered terminating action for the inspection requirements of paragraph (g) of this AD. New Requirements of This AD Determine Elevator Group Number or Elevator Configuration Number (i) Within 1,000 flight hours or 750 flight cycles after the effective date of this AD, whichever occurs first, determine the elevator group number or the elevator configuration number in accordance with Appendix A of Boeing Alert Service Bulletin 737–55A1078, dated October 27, 2005. Initial and Repetitive Inspections (j) At the applicable time specified in Tables 2 and 3 of paragraph 1.E. ‘‘Compliance’’ of Boeing Alert Service Bulletin 737–55A1078, dated October 27, 2005, except where the alert service bulletin specifies a compliance time from the release date of the alert service bulletin, this AD requires the compliance time after the effective date of this AD: Do the applicable initial detailed and special detailed inspections for interlaminar corrosion, cracking, delamination, or disbonding in the rear spar by doing all the applicable actions specified in Parts I, II, and III of the Accomplishment Instructions of Boeing Alert Service Bulletin 737–55A1078, dated October 27, 2005; except where step 3. of Part III of the alert service bulletin specifies to do a special detailed inspection for spar interlaminar corrosion as given in Figure 3, this AD requires all actions specified in Figure 3 to be done (a detailed inspection for interlaminar corrosion and disbonding and a special detailed inspection for interlaminar corrosion and delamination). Doing the initial inspections terminates the requirements of paragraphs (f) and (g) of this AD. (k) Repeat the inspections specified in paragraph (j) of this AD at the applicable time specified in Tables 4 and 5 of paragraph 1.E. ‘‘Compliance’’ of Boeing Alert Service Bulletin 737–55A1078, dated October 27, 2005; except where Table B.4 in Appendix B of the alert service bulletin specifies compliance times in flight hours or flight cycles, this AD requires the actions specified in Table B.4 be done at the earlier of the compliance times in flight hours or flight cycles. Corrective Actions (l) If any interlaminar corrosion, cracking, delamination, or disbonding is found during any inspection required by this AD: Before further flight, use Appendix C of Boeing Alert Service Bulletin 737–55A1078, dated October 27, 2005, to determine the permitted repairs, and do the applicable repair, including related investigative and corrective actions, by doing all the applicable actions specified in Parts IV through VIII (Interim Repairs) and Part IX (Time-limited Repair) of the Accomplishment Instructions of the alert service bulletin, except as provided by paragraphs (n) and (o) of this AD. (m) If the time-limited repair specified in Part IX of the Accomplishment Instructions of Boeing Alert Service Bulletin 737– 55A1078, dated October 27, 2005, is done: At the time specified in Table 6 of paragraph 1.E. ‘‘Compliance’’ of the alert service bulletin, do the applicable repair, including related investigative and corrective actions, by doing all the applicable actions specified in Parts IV through VI (Interim Repairs) of the alert service bulletin. Thereafter, do the repetitive inspections specified in paragraph (k) of this AD. (n) Where Boeing Alert Service Bulletin 737–55A1078, dated October 27, 2005, specifies to contact the manufacturer for appropriate action for the inspar rib replacement or for more instructions if any crack is outside the limit specified in the service bulletin: Before further flight, repair in accordance with a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA; or using a method approved in accordance with paragraph (p) of this AD. (o) Where step 3.a. of Part III of the Accomplishment Instructions of Boeing Alert Service Bulletin 737–55A1078, dated October 27, 2005, specifies that if interlaminar corrosion is found, spar replacement is required, this AD requires spar replacement if interlaminar corrosion, delamination, or disbonding is found. Where step 3.C. of Appendix C of the alert service bulletin specifies that for laminated spars that have interlaminar corrosion, only repair options B, C, and D are permitted, this AD specifies that for laminated spars that have interlaminar corrosion, delamination, or disbonding, only repair options B, C, and D are permitted. Alternative Methods of Compliance (AMOCs) (p)(1) The Manager, ACO, FAA, 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 § 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) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD, if it is approved by an Authorized Representative for the Boeing Commercial Airplanes Delegation Option Authorization Organization who has been authorized by the Manager, Seattle ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) Accomplishing the Interim Repair Option C or D specified in the Accomplishment Instructions of Boeing Alert Service Bulletin 737–55A1078, dated October 27, 2005, is an AMOC for the structural modification requirements specified in paragraph A. of AD 90–06–02, amendment 39–6489, that are done in accordance with Boeing Alert Service Bulletins 737–55-A1020 or 737–55A1020, or Boeing Service Bulletin 737–55–1022 only. All provisions of AD 90– 06–02 that do not specifically reference these service bulletins remain fully applicable and must be complied with. (5) AMOCs approved previously in accordance with AD 76–11–05 R1, are approved as AMOCs for the corresponding provisions of paragraphs (f) through (h) of this AD. Material Incorporated by Reference (q) You must use the applicable service bulletins listed in Table 1 of this AD to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of these documents in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. TABLE 1.—MATERIAL INCORPORATED BY REFERENCE Service Bulletin rmajette on PROD1PC67 with RULES Boeing Boeing Boeing Boeing Boeing Revision level Alert Service Bulletin 737–55A1020 .............................................................................................. Alert Service Bulletin 737–55A1020 .............................................................................................. Alert Service Bulletin 737–55A1020 .............................................................................................. Alert Service Bulletin 737–55A1078 .............................................................................................. Service Bulletin 737–55–1022 ....................................................................................................... Date 1 ....................... 2 ....................... 3 ....................... Original ............. Original ............. August 20, 1976. February 11, 1977. December 22, 1988. October 27, 2005. April 15, 1977. Boeing Alert Service Bulletin 737–55– A1020, Revision 1, dated August 20, 1976, contains the following effective pages: VerDate Aug<31>2005 15:22 Jul 14, 2006 Jkt 208001 PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 E:\FR\FM\17JYR1.SGM 17JYR1 40394 Federal Register / Vol. 71, No. 136 / Monday, July 17, 2006 / Rules and Regulations Page No. Revision level shown on page Date shown on page 1, 11–27 ...................................................................................................................................................... 2–10 ............................................................................................................................................................ 1 ....................... Original ............. August 20, 1976. May 20, 1976. Page No. Revision level shown on page Date shown on page 1, 3, 6, 10–12, 14, 16, 25 ........................................................................................................................... 2, 4, 5, 7–9 ................................................................................................................................................. 13, 15, 17–24, 26, 27 ................................................................................................................................. 2 ....................... Original ............. 1 ....................... February 11, 1977. May 20, 1976. August 20, 1976. Boeing Alert Service Bulletin 737–55– A1020, Revision 2, dated February 11, 1977, contains the following effective pages: Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124– 2207, 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 http://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 http:// www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on July 3, 2006. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 06–6152 Filed 7–14–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 71 [Docket No. FAA–2006–24813; Airspace Docket No. 06–AAL–16] Modification of Legal Description of Class D and E Airspace; Fairbanks, Fort Wainwright Army Airfield, AK Federal Aviation Administration (FAA), DOT. ACTION: Direct final rule Correction; request for comments. rmajette on PROD1PC67 with RULES AGENCY: SUMMARY: The U.S. Army will soon be changing the name of Fort (Ft.) Wainwright Army Airfield (AAF) to Ladd AAF. This action amends the airport name accordingly for each of the Class D and Class E airspace descriptions in FAA Order 7400.9N. This action also amends an altitude omission which currently does not exist in the FAA Order 7400.9N. This action also redefines the airspace description VerDate Aug<31>2005 15:22 Jul 14, 2006 Jkt 208001 to account for recent updates to the airfield coordinates. DATES: This direct final rule is effective on 0901 UTC, November 23, 2006. Comments for inclusion in the Rules Docket must be received on or before August 16, 2006. ADDRESSES: Send comments on this proposal to the Docket Management System, U.S. Department of Transportation, Room Plaza 401, 400 Seventh Street, SW., Washington, DC 20590–0001. You must identify the docket number FAA–2006–24813/ Airspace Docket No. 06–AAL–16, at the beginning of your comments. You may also submit comments on the Internet at http://dms.dot.gov. You may review the public docket containing the proposal, any comments received, and any final disposition in person in the Docket Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone 1–800–647–5527) is on the plaza level of the Department of Transportation NASSIF Building at the above address. FOR FURTHER INFORMATION CONTACT: Gary Rolf, Federal Aviation Administration, 222 West 7th Avenue, Box 14, Anchorage, AK 99513–7587; telephone number (907) 271–5898; fax: (907) 271– 2850; e-mail: gary.ctr.rolf@faa.gov. Internet address: http:// www.alaska.faa.gov/at. SUPPLEMENTARY INFORMATION: The coordinates for this airspace docket are based on North American Datum 83. The Class D airspace and Class E airspace areas designated as 700/1200 foot transition areas are published in paragraph 5000 and 6005 respectively, in FAA Order 7400.9N, Airspace Designations and Reporting Points, dated September 1, 2005, and effective September 15, 2005, which is incorporated by reference in 14 CFR 71.1. The Class D and E airspace designations listed in this document would be published subsequently in the PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 Order. Additionally, the present exclusionary clause listed in the Class E5 description is removed. The exclusionary language is redundant and therefore, unnecessary. The Direct Final Rule Procedure The FAA anticipates that this regulation will not result in adverse or negative comment and therefore, is issuing it as a direct final rule. Previous actions of this nature have not been controversial and have not resulted in adverse comments or objections. Unless a written adverse or negative comment, or written notice of intent to submit an adverse or negative comment is received within the comment period, the regulation will become effective on the date specified above. After the close of the comment period, the FAA will publish a document in the Federal Register indicating that no adverse or negative comments were received and confirming the date on which the final rule will become effective. If the FAA does receive, within the comment period, an adverse or negative comment, or written notice of intent to submit such a comment, a document withdrawing the direct final rule will be published in the Federal Register, and a notice of proposed rulemaking may be published with a new comment period. Comments Invited Interested parties are invited to participate in this rulemaking by submitting such written data, views, or arguments, as they may desire. Comments that provide the factual basis supporting the views and suggestions presented are particularly helpful in developing reasoned regulatory decisions on the proposal. Comments are specifically invited on the overall regulatory, aeronautical, economic, environmental, and energy-related aspects of the proposal. Communications should identify both E:\FR\FM\17JYR1.SGM 17JYR1

Agencies

[Federal Register Volume 71, Number 136 (Monday, July 17, 2006)]
[Rules and Regulations]
[Pages 40391-40394]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-6152]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-24432; Directorate Identifier 2005-NM-227-AD; 
Amendment 39-14678; AD 2006-14-07]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 737-100, -200, and -200C 
Series 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 Boeing Model 737 series airplanes. That 
AD currently requires inspection of the elevator tab inboard hinge 
support structure to detect fatigue cracking and corrective action if 
necessary. That AD also provides an optional terminating action. This 
new AD adds airplanes to the applicability and requires new repetitive 
inspections. For airplanes having elevators with laminated rear spars, 
this new AD requires repetitive inspections for interlaminar corrosion, 
delamination, or disbonding in the rear spar, repetitive inspections 
for cracking in the spar web, and repair including related 
investigative/corrective actions if necessary. For airplanes having 
elevators with solid rear spars, this new AD requires repetitive 
inspections for cracking in the spar web and repair including related 
investigative/corrective actions if necessary. This AD results from 
reports of cracks in the elevator rear spar web at the tab hinge 
bracket locations. We are issuing this AD to detect and correct 
cracking, corrosion, interlaminar corrosion, delamination, and 
disbonding in the elevator rear spar, which may reduce elevator 
stiffness and lead to in-flight vibration. In-flight vibration may lead 
to elevator and horizontal stabilizer damage and reduced 
controllability of the airplane.

DATES: This AD becomes effective August 21, 2006.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of August 21, 
2006.

ADDRESSES: You may examine the AD docket on the Internet at http://
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, P.O. Box 3707, Seattle, 
Washington 98124-2207, for service information identified in this AD.

FOR FURTHER INFORMATION CONTACT: Nancy Marsh, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
917-6440; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION:

Examining the Docket

    You may examine the airworthiness directive (AD) docket on the 
Internet at http://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 76-11-05 R1, amendment 
39-6234 (54 FR 25709, June 19, 1989). The existing AD applies to 
certain Boeing Model 737 series airplanes. That NPRM was published in 
the Federal Register on April 13, 2006 (71 FR 19144). That NPRM 
proposed to continue to require inspection of the elevator tab inboard 
hinge support structure to detect fatigue cracking and corrective 
action if necessary. That NPRM also proposed to continue to provide an 
optional terminating action for the existing inspections. That NPRM 
proposed to add airplanes to the applicability and to require new 
repetitive inspections. For airplanes having elevators with laminated 
rear spars, that NPRM proposed to require repetitive inspections for 
interlaminar corrosion, delamination, or disbonding

[[Page 40392]]

in the rear spar, repetitive inspections for cracking in the spar web, 
and repair including related investigative/corrective actions if 
necessary. For airplanes having elevators with solid rear spars, that 
NPRM proposed to require repetitive inspections for cracking in the 
spar web and repair including related investigative/corrective actions 
if necessary.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. No comments have been received on the NPRM or 
on the determination of the cost to the public.

Conclusion

    We have carefully reviewed the available data and determined that 
air safety and the public interest require adopting the AD as proposed.

Costs of Compliance

    There are about 1,355 airplanes of the affected design in the 
worldwide fleet. The following table provides the estimated costs for 
U.S. operators to comply with this AD.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                               Average                        Number of U.S.-
             Action                  Work     labor rate   Cost per airplane    registered        Fleet cost
                                    hours      per hour                          airplanes
----------------------------------------------------------------------------------------------------------------
Inspection, per inspection cycle     10-100          $80  $800-$8,000, per               230  $184,000-$1,840,00
                                                           inspection cycle.                   0, 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 39-6234 (54 FR 25709, June 19, 1989) and by adding 
the following new airworthiness directive (AD):

2006-14-07 Boeing: Amendment 39-14678. Docket No. FAA-2006-24432; 
Directorate Identifier 2005-NM-227-AD.

Effective Date

    (a) This AD becomes effective August 21, 2006.

Affected ADs

    (b) This AD supersedes AD 76-11-05 R1.

Applicability

    (c) This AD applies to Boeing Model 737-100, -200, and -200C 
series airplanes, certificated in any category; as identified in 
Boeing Alert Service Bulletin 737-55A1078, dated October 27, 2005.

Unsafe Condition

    (d) This AD results from reports of cracks in the elevator rear 
spar web at the tab hinge bracket locations. We are issuing this AD 
to detect and correct cracking, corrosion, interlaminar corrosion, 
delamination, and disbonding in the elevator rear spar, which may 
reduce elevator stiffness and lead to in-flight vibration. In-flight 
vibration may lead to elevator and horizontal stabilizer damage and 
reduced 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 Certain Requirements of AD 76-11-05 R1

    (f) For Model 737-100, -200, and -200C series airplanes, line 
number 001 through 491 inclusive: Within the next 300 hours time-in-
service after July 24, 1989 (the effective date of AD 76-11-05 R1), 
unless accomplished within the last 700 hours time-in-service, and 
at intervals thereafter not to exceed 1,000 hours time-in-service, 
conduct the inspection required by paragraph (g) of this AD. 
Accomplishing the initial inspections specified in paragraph (j) of 
this AD terminates the requirements of this paragraph.
    (g) For Model 737-100, -200, and -200C series airplanes, line 
number 001 through 491 inclusive: At the times specified in 
paragraph (f) of this AD, inspect for excessive deflection of the 
elevator tab, right and left hand, in accordance with the inspection 
procedures specified in Section III, Part I, paragraphs C. and D., 
of Boeing Alert Service Bulletin 737-55-A1020, Revision 1, dated 
August 20, 1976; Revision 2, dated February 11, 1977; or 737-
55A1020, Revision 3, dated December 22, 1988. If the elevator tab-
to-elevator relative deflection exceeds 1/10 inch, prior to further 
flight, modify the elevator in accordance with paragraph (h) of this 
AD. Accomplishing the initial inspections specified in paragraph (j) 
of this AD terminates the requirements of this paragraph.

[[Page 40393]]

    (h) For Model 737-100, -200, and -200C series airplanes, line 
number 001 through 491 inclusive: Installation of one of the 
modifications specified in Boeing Alert Service Bulletin 737-55-
A1020, Revision 1, dated August 20, 1976; 737-55-A1020, Revision 2, 
dated February 11, 1977; or 737-55A1020, Revision 3, dated December 
22, 1988; Section III, Part II, including installation of the bolt 
retainer clips or the preventive modification specified in Boeing 
Service Bulletin 737-55-1022, Section III, Part II, dated April 15, 
1977; is considered terminating action for the inspection 
requirements of paragraph (g) of this AD.

New Requirements of This AD

Determine Elevator Group Number or Elevator Configuration Number

    (i) Within 1,000 flight hours or 750 flight cycles after the 
effective date of this AD, whichever occurs first, determine the 
elevator group number or the elevator configuration number in 
accordance with Appendix A of Boeing Alert Service Bulletin 737-
55A1078, dated October 27, 2005.

Initial and Repetitive Inspections

    (j) At the applicable time specified in Tables 2 and 3 of 
paragraph 1.E. ``Compliance'' of Boeing Alert Service Bulletin 737-
55A1078, dated October 27, 2005, except where the alert service 
bulletin specifies a compliance time from the release date of the 
alert service bulletin, this AD requires the compliance time after 
the effective date of this AD: Do the applicable initial detailed 
and special detailed inspections for interlaminar corrosion, 
cracking, delamination, or disbonding in the rear spar by doing all 
the applicable actions specified in Parts I, II, and III of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
55A1078, dated October 27, 2005; except where step 3. of Part III of 
the alert service bulletin specifies to do a special detailed 
inspection for spar interlaminar corrosion as given in Figure 3, 
this AD requires all actions specified in Figure 3 to be done (a 
detailed inspection for interlaminar corrosion and disbonding and a 
special detailed inspection for interlaminar corrosion and 
delamination). Doing the initial inspections terminates the 
requirements of paragraphs (f) and (g) of this AD.
    (k) Repeat the inspections specified in paragraph (j) of this AD 
at the applicable time specified in Tables 4 and 5 of paragraph 1.E. 
``Compliance'' of Boeing Alert Service Bulletin 737-55A1078, dated 
October 27, 2005; except where Table B.4 in Appendix B of the alert 
service bulletin specifies compliance times in flight hours or 
flight cycles, this AD requires the actions specified in Table B.4 
be done at the earlier of the compliance times in flight hours or 
flight cycles.

Corrective Actions

    (l) If any interlaminar corrosion, cracking, delamination, or 
disbonding is found during any inspection required by this AD: 
Before further flight, use Appendix C of Boeing Alert Service 
Bulletin 737-55A1078, dated October 27, 2005, to determine the 
permitted repairs, and do the applicable repair, including related 
investigative and corrective actions, by doing all the applicable 
actions specified in Parts IV through VIII (Interim Repairs) and 
Part IX (Time-limited Repair) of the Accomplishment Instructions of 
the alert service bulletin, except as provided by paragraphs (n) and 
(o) of this AD.
    (m) If the time-limited repair specified in Part IX of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
55A1078, dated October 27, 2005, is done: At the time specified in 
Table 6 of paragraph 1.E. ``Compliance'' of the alert service 
bulletin, do the applicable repair, including related investigative 
and corrective actions, by doing all the applicable actions 
specified in Parts IV through VI (Interim Repairs) of the alert 
service bulletin. Thereafter, do the repetitive inspections 
specified in paragraph (k) of this AD.
    (n) Where Boeing Alert Service Bulletin 737-55A1078, dated 
October 27, 2005, specifies to contact the manufacturer for 
appropriate action for the inspar rib replacement or for more 
instructions if any crack is outside the limit specified in the 
service bulletin: Before further flight, repair in accordance with a 
method approved by the Manager, Seattle Aircraft Certification 
Office (ACO), FAA; or using a method approved in accordance with 
paragraph (p) of this AD.
    (o) Where step 3.a. of Part III of the Accomplishment 
Instructions of Boeing Alert Service Bulletin 737-55A1078, dated 
October 27, 2005, specifies that if interlaminar corrosion is found, 
spar replacement is required, this AD requires spar replacement if 
interlaminar corrosion, delamination, or disbonding is found. Where 
step 3.C. of Appendix C of the alert service bulletin specifies that 
for laminated spars that have interlaminar corrosion, only repair 
options B, C, and D are permitted, this AD specifies that for 
laminated spars that have interlaminar corrosion, delamination, or 
disbonding, only repair options B, C, and D are permitted.

Alternative Methods of Compliance (AMOCs)

    (p)(1) The Manager, ACO, FAA, 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 Sec.  
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) An AMOC that provides an acceptable level of safety may be 
used for any repair required by this AD, if it is approved by an 
Authorized Representative for the Boeing Commercial Airplanes 
Delegation Option Authorization Organization who has been authorized 
by the Manager, Seattle ACO, to make those findings. For a repair 
method to be approved, the repair must meet the certification basis 
of the airplane, and the approval must specifically refer to this 
AD.
    (4) Accomplishing the Interim Repair Option C or D specified in 
the Accomplishment Instructions of Boeing Alert Service Bulletin 
737-55A1078, dated October 27, 2005, is an AMOC for the structural 
modification requirements specified in paragraph A. of AD 90-06-02, 
amendment 39-6489, that are done in accordance with Boeing Alert 
Service Bulletins 737-55-A1020 or 737-55A1020, or Boeing Service 
Bulletin 737-55-1022 only. All provisions of AD 90-06-02 that do not 
specifically reference these service bulletins remain fully 
applicable and must be complied with.
    (5) AMOCs approved previously in accordance with AD 76-11-05 R1, 
are approved as AMOCs for the corresponding provisions of paragraphs 
(f) through (h) of this AD.

Material Incorporated by Reference

    (q) You must use the applicable service bulletins listed in 
Table 1 of this AD to perform the actions that are required by this 
AD, unless the AD specifies otherwise. The Director of the Federal 
Register approved the incorporation by reference of these documents 
in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.

                                  Table 1.--Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
            Service Bulletin                       Revision level                           Date
----------------------------------------------------------------------------------------------------------------
Boeing Alert Service Bulletin 737-        1...............................  August 20, 1976.
 55A1020.
Boeing Alert Service Bulletin 737-        2...............................  February 11, 1977.
 55A1020.
Boeing Alert Service Bulletin 737-        3...............................  December 22, 1988.
 55A1020.
Boeing Alert Service Bulletin 737-        Original........................  October 27, 2005.
 55A1078.
Boeing Service Bulletin 737-55-1022.....  Original........................  April 15, 1977.
----------------------------------------------------------------------------------------------------------------

    Boeing Alert Service Bulletin 737-55-A1020, Revision 1, dated 
August 20, 1976, contains the following effective pages:

[[Page 40394]]



----------------------------------------------------------------------------------------------------------------
                Page No.                    Revision level shown on page             Date shown on page
----------------------------------------------------------------------------------------------------------------
1, 11-27................................  1...............................  August 20, 1976.
2-10....................................  Original........................  May 20, 1976.
----------------------------------------------------------------------------------------------------------------

    Boeing Alert Service Bulletin 737-55-A1020, Revision 2, dated 
February 11, 1977, contains the following effective pages:

----------------------------------------------------------------------------------------------------------------
                Page No.                    Revision level shown on page             Date shown on page
----------------------------------------------------------------------------------------------------------------
1, 3, 6, 10-12, 14, 16, 25..............  2...............................  February 11, 1977.
2, 4, 5, 7-9............................  Original........................  May 20, 1976.
13, 15, 17-24, 26, 27...................  1...............................  August 20, 1976.
----------------------------------------------------------------------------------------------------------------

    Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, 
Washington 98124-2207, 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 http://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 http://www.archives.gov/federal_register/
code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on July 3, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 06-6152 Filed 7-14-06; 8:45 am]
BILLING CODE 4910-13-P