Airworthiness Directives; Boeing Model 767-200 and -300 Series Airplanes, 38821-38823 [05-13222]

Download as PDF Federal Register / Vol. 70, No. 128 / Wednesday, July 6, 2005 / Proposed Rules Part Installation (g) As of the effective date of this AD, no person may install, on any airplane, an aileron control quadrant override assembly that has not been modified in accordance with the requirements of this AD. Alternative Methods of Compliance (AMOCs) (h) The Manager, Seattle Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. Issued in Renton, Washington, on June 27, 2005. Kevin M. Mullin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–13225 Filed 7–5–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–21715; Directorate Identifier 2004–NM–277–AD] RIN 2120–AA64 Airworthiness Directives; Boeing Model 767–200 and –300 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for certain Boeing Model 767–200 and –300 series airplanes. This proposed AD would require measuring the turnbuckle gap of the inflation cylinder of the offwing emergency escape slide; corrective action if necessary; and installing a safety device on the inflation cylinder of the off-wing emergency escape slide. This proposed AD is prompted by a report indicating that the inflation trigger cable may inadvertently disconnect from the inflation turnbuckle of the inflation cylinder of the off-wing emergency escape slide, due to incorrect spacing of the cable insertion gap; and additional reports indicating that the pull force increase mechanism on the off-wing charged cylinder assemblies of the escape slide may be inadvertently disengaged. We are proposing this AD to prevent failed deployment of the emergency escape slide during an emergency, which could impede an evacuation and result in injury to passengers or airplane crewmembers, or VerDate jul<14>2003 15:27 Jul 05, 2005 Jkt 205001 inadvertent inflation and loss of an emergency escape slide during flight, which could result in possible structural damage to the airplane. DATES: We must receive comments on this proposed AD by August 22, 2005. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD. • DOT Docket Web site: Go to http: //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. • By fax: (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. For service information identified in this proposed AD, contact Boeing Commercial Airplanes, PO Box 3707, Seattle, Washington 98124–2207. You can examine the contents of this 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., room PL–401, on the plaza level of the Nassif Building, Washington, DC. This docket number is FAA–2005– 21715; the directorate identifier for this docket is 2004–NM–277–AD. FOR FURTHER INFORMATION CONTACT: Sue Rosanske, Aerospace Engineer, Cabin Safety and Environmental Systems Branch, ANM–150S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 917–6448; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to submit any relevant written data, views, or arguments regarding this proposed AD. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA– 2005–21715; Directorate Identifier 2004–NM–277–AD’’ in the subject line of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments submitted by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 38821 dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Using the search function of that website, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You can review DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you can visit https:// dms.dot.gov. Examining the Docket You can examine the 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 DOT street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the DMS receives them. Discussion We have received a report indicating that, during a pre-delivery slide deployment check, the inflation trigger cable inadvertently disconnected from the inflation trigger turnbuckle of the inflation cylinder of the off-wing emergency escape slide on a Boeing Model 767–300 series airplane. Further investigation revealed that the cable insertion gap in the turnbuckle (referred to as the ‘‘turnbuckle gap’’) of certain inflation cylinders was not crimped per the engineering drawing specification. The gap measured approximately 0.070inch, instead of the 0.040-inch maximum allowable spacing. We also received reports that operators have found the pull force increase mechanism (PFIM) on the inflation cylinder of the off-wing emergency escape slide incorrectly set to the ‘‘DISENGAGED’’ position on Boeing Model 767–200 and –300 series airplanes. If the PFIM retainer spring is not positioned in the ‘‘ENGAGED’’ position, airframe flexing could result in inadvertent actuation of the inflation cylinder and subsequent inflation of the off-wing emergency escape slide. These conditions, if not corrected, could result in failed deployment of the emergency escape slide during an emergency, which could impede an evacuation and result in injury to passengers or airplane crewmembers, or E:\FR\FM\06JYP1.SGM 06JYP1 38822 Federal Register / Vol. 70, No. 128 / Wednesday, July 6, 2005 / Proposed Rules inadvertent inflation and loss of an emergency escape slide during flight, which could result in possible structural damage to the airplane. Relevant Service Information We have reviewed Boeing Special Attention Service Bulletin 767–25– 0358, dated September 18, 2003. The service bulletin describes procedures for measuring the turnbuckle gap on the inflation cylinder of the off-wing emergency escape slides (to ensure it meets the maximum allowable spacing limit), and performing corrective actions if necessary. The corrective actions include crimping the gap to the correct spacing, making sure the turnbuckle can rotate around the cable; and replacing the adjustable bottle cable assembly with a new assembly if the turnbuckle cannot rotate. Special Attention Service Bulletin 767–25–0358 refers to Goodrich Service Bulletin 130104–25–342, dated July 23, 2003, as an additional source of service information. We have also reviewed Boeing Special Attention Service Bulletin 767–25– 0317, dated June 27, 2002. The service bulletin describes procedures for installing a safety device on the PFIM of the inflation cylinder of the off-wing emergency escape slide system and partmarking the inflation cylinder if applicable. Special Attention Service Bulletin 767–25–0317 refers to Goodrich Service Bulletin 130104–25–328, Revision 1, dated July 23, 2003, as an additional source of service information. Accomplishing the actions specified in the Boeing service information is intended to adequately address the unsafe condition. FAA’s Determination and Requirements of the Proposed AD We have evaluated all pertinent information and identified an unsafe condition that is likely to exist or develop on other airplanes of this same type design. Therefore, we are proposing this AD, which would require accomplishing the actions specified in the Boeing service information described previously, except as discussed under ‘‘Difference Between the Proposed AD and Boeing Service Information.’’ Difference Between the Proposed AD and Boeing Service Information The service bulletins recommend that the actions therein be accomplished ‘‘at the next normally scheduled maintenance period when manpower, materials, and facilities are available.’’ We find that such a non-specific VerDate jul<14>2003 15:27 Jul 05, 2005 Jkt 205001 compliance time may not ensure that the proposed actions are accomplished in a timely manner. In developing an appropriate compliance time for these actions, we considered the safety implications, operators’ normal maintenance schedules, and the compliance time recommended by the airplane manufacturer. In consideration of these items, we have determined that 18 months represents an appropriate interval of time wherein the proposed actions can be accomplished during scheduled maintenance intervals for the majority of affected operators, and an acceptable level of safety can be maintained. This compliance time is consistent with the recommendation of the airplane manufacturer. Clarification of ‘‘Concurrent’’ Service Information The Boeing service bulletins specify concurrent accomplishment of the Goodrich service bulletins; however, this proposed AD refers to the Goodrich service bulletins as additional sources of service information. Costs of Compliance There are about 696 airplanes of the affected design in the worldwide fleet. This proposed AD would affect about 297 airplanes of U.S. registry. The proposed inspection would take about 1 work hour per airplane, at an average labor rate of $65 per work hour. Based on these figures, the estimated cost of the proposed inspection for U.S. operators is $19,305, or $65 per airplane. The proposed safety device installation would take about 3 work hours per airplane, at an average labor rate of $65 per work hour. Required parts cost would be minimal. Based on these figures, the estimated cost of the proposed installation for U.S. operators is $57,915, or $195 per airplane. 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 PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 the proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the 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 proposed AD. 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, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): Boeing: Docket No. FAA–2005–21715; Directorate Identifier 2004–NM–277–AD. Comments Due Date (a) The Federal Aviation Administration (FAA) must receive comments on this AD action by August 22, 2005. Affected ADs (b) None. Applicability (c) This AD applies to Boeing Model 767– 200 and –300 series airplanes; certificated in any category; equipped with off-wing E:\FR\FM\06JYP1.SGM 06JYP1 Federal Register / Vol. 70, No. 128 / Wednesday, July 6, 2005 / Proposed Rules emergency escape slides; as identified in Boeing Special Attention Service Bulletin 767–25–0358, dated September 18, 2003; and Boeing Special Attention Service Bulletin 767–25–0317, dated June 27, 2002. Unsafe Condition (d) This AD was prompted by a report indicating that the inflation trigger cable may inadvertently disconnect from the inflation turnbuckle of the inflation cylinder of the offwing emergency escape slide, due to incorrect spacing of the cable insertion gap; and additional reports indicating that the pull force increase mechanism (PFIM) on the off-wing charged cylinder assemblies of the escape slide may be inadvertently disengaged. We are issuing this AD to prevent failed deployment of the emergency escape slide during an emergency, which could impede an evacuation and result in injury to passengers or airplane crewmembers, or inadvertent inflation and loss of an emergency escape slide during flight, which could result in possible structural damage to 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. Measurement/Corrective Action (f) Within 18 months after the effective date of this AD: Accomplish the actions specified in paragraphs (f)(1) and (f)(2) of this AD. (1) Measure the turnbuckle gap of the inflation cylinder of the off-wing emergency escape slides to ensure it meets the maximum allowable spacing limit and do applicable corrective actions by doing all the actions specified in the Accomplishment Instructions of Boeing Special Attention Service Bulletin 767–25–0358, dated September 18, 2003. Accomplish any corrective action before further flight in accordance with the service bulletin. (2) Install a safety device on the PFIM of the inflation cylinder of the off-wing emergency escape slides, and part-mark the inflation cylinder as applicable, by doing all the actions specified in the Accomplishment Instructions of Boeing Special Attention Service Bulletin 767–25–0317, dated June 27, 2002. Note 1: Goodrich Service Bulletins 130104–25–342, dated July 23, 2003; and 130104–25–328, Revision 1, dated July 23, 2003; may be used as additional sources of service information for accomplishing the actions. Parts Installation (g) As of the effective date of this AD, no person may install an inflation cylinder of the off-wing emergency escape slides on any airplane, unless it has been modified according to paragraph (f) of this AD. Alternative Methods of Compliance (AMOCs) (h) The Manager, Seattle Aircraft Certification Office, FAA, has the authority to approve AMOCs for this AD, if requested in VerDate jul<14>2003 15:27 Jul 05, 2005 Jkt 205001 accordance with the procedures found in 14 CFR 39.19. Issued in Renton, Washington, on June 24, 2005. Michael J. Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–13222 Filed 7–5–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2004–19540; Directorate Identifier 2004–NM–110–AD] RIN 2120–AA64 Airworthiness Directives; Boeing Model 757 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of comment period. AGENCY: SUMMARY: The FAA is revising an earlier proposed airworthiness directive (AD) for certain Boeing Model 757 airplanes. The original NPRM would have required inspections of certain wire bundles in the left and right engine-towing aft fairings for discrepancies, and related investigative and corrective actions if necessary. The original NPRM was prompted by a report indicating that a circuit breaker for the fuel shutoff valve tripped due to a wire that chafed against the structure in the flammable leakage zone of the aft fairing, causing a short circuit. This action revises the original NPRM by adding a new requirement for installing back-to-back p-clamps between the wire and hydraulic supply tube at the aft end of the right-hand strut only; and associated re-routing of the wire bundles, if necessary; and adding airplanes to the applicability. This action also clarifies the applicability specified in the original NPRM. We are proposing this supplemental NPRM to prevent chafing between the wire bundle and the structure of the aft fairing, which could result in electrical arcing and subsequent ignition of flammable vapors and possible uncontrollable fire. DATES: We must receive comments on this supplemental NPRM by August 1, 2005. ADDRESSES: Use one of the following addresses to submit comments on this supplemental NPRM. PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 38823 • DOT Docket Web site: Go to http:/ /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. • Fax: (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. For service information identified in this proposed AD, contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207. You can examine the contents of this 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., room PL–401, on the plaza level of the Nassif Building, Washington, DC. This docket number is FAA–2004– 19540; the directorate identifier for this docket is 2004–NM–110–AD. FOR FURTHER INFORMATION CONTACT: Thomas Thorson, Aerospace Engineer, Propulsion Branch, ANM–140S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 917–6508; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to submit any relevant written data, views, or arguments regarding this supplemental NPRM. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA–2004–19540; Directorate Identifier 2004–NM–110– AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this supplemental NPRM. We will consider all comments received by the closing date and may amend this supplemental NPRM in light of those comments. We will post all comments submitted, without change, to https://dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this supplemental NPRM. Using the search function of our docket Web site, anyone can find and read the comments in any of our dockets, including the E:\FR\FM\06JYP1.SGM 06JYP1

Agencies

[Federal Register Volume 70, Number 128 (Wednesday, July 6, 2005)]
[Proposed Rules]
[Pages 38821-38823]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-13222]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-21715; Directorate Identifier 2004-NM-277-AD]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 767-200 and -300 Series 
Airplanes

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

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for certain Boeing Model 767-200 and -300 series airplanes. This 
proposed AD would require measuring the turnbuckle gap of the inflation 
cylinder of the off-wing emergency escape slide; corrective action if 
necessary; and installing a safety device on the inflation cylinder of 
the off-wing emergency escape slide. This proposed AD is prompted by a 
report indicating that the inflation trigger cable may inadvertently 
disconnect from the inflation turnbuckle of the inflation cylinder of 
the off-wing emergency escape slide, due to incorrect spacing of the 
cable insertion gap; and additional reports indicating that the pull 
force increase mechanism on the off-wing charged cylinder assemblies of 
the escape slide may be inadvertently disengaged. We are proposing this 
AD to prevent failed deployment of the emergency escape slide during an 
emergency, which could impede an evacuation and result in injury to 
passengers or airplane crewmembers, or inadvertent inflation and loss 
of an emergency escape slide during flight, which could result in 
possible structural damage to the airplane.

DATES: We must receive comments on this proposed AD by August 22, 2005.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
     DOT Docket Web site: Go to http: //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.
     By fax: (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.
    For service information identified in this proposed AD, contact 
Boeing Commercial Airplanes, PO Box 3707, Seattle, Washington 98124-
2207.
    You can examine the contents of this 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., room PL-401, 
on the plaza level of the Nassif Building, Washington, DC. This docket 
number is FAA-2005-21715; the directorate identifier for this docket is 
2004-NM-277-AD.

FOR FURTHER INFORMATION CONTACT: Sue Rosanske, Aerospace Engineer, 
Cabin Safety and Environmental Systems Branch, ANM-150S, FAA, Seattle 
Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, 
Washington 98055-4056; telephone (425) 917-6448; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to submit any relevant written data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-2005-21715; 
Directorate Identifier 2004-NM-277-AD'' in the subject line of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed AD. We will 
consider all comments submitted by the closing date and may amend the 
proposed AD in light of those comments.
    We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this proposed AD. Using the search function of 
that website, anyone can find and read the comments in any of our 
dockets, including the name of the individual who sent the comment (or 
signed the comment on behalf of an association, business, labor union, 
etc.). You can review DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or you 
can visit https://dms.dot.gov.

Examining the Docket

    You can examine the 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 DOT 
street address stated in the ADDRESSES section. Comments will be 
available in the AD docket shortly after the DMS receives them.

Discussion

    We have received a report indicating that, during a pre-delivery 
slide deployment check, the inflation trigger cable inadvertently 
disconnected from the inflation trigger turnbuckle of the inflation 
cylinder of the off-wing emergency escape slide on a Boeing Model 767-
300 series airplane. Further investigation revealed that the cable 
insertion gap in the turnbuckle (referred to as the ``turnbuckle gap'') 
of certain inflation cylinders was not crimped per the engineering 
drawing specification. The gap measured approximately 0.070-inch, 
instead of the 0.040-inch maximum allowable spacing.
    We also received reports that operators have found the pull force 
increase mechanism (PFIM) on the inflation cylinder of the off-wing 
emergency escape slide incorrectly set to the ``DISENGAGED'' position 
on Boeing Model 767-200 and -300 series airplanes. If the PFIM retainer 
spring is not positioned in the ``ENGAGED'' position, airframe flexing 
could result in inadvertent actuation of the inflation cylinder and 
subsequent inflation of the off-wing emergency escape slide.
    These conditions, if not corrected, could result in failed 
deployment of the emergency escape slide during an emergency, which 
could impede an evacuation and result in injury to passengers or 
airplane crewmembers, or

[[Page 38822]]

inadvertent inflation and loss of an emergency escape slide during 
flight, which could result in possible structural damage to the 
airplane.

Relevant Service Information

    We have reviewed Boeing Special Attention Service Bulletin 767-25-
0358, dated September 18, 2003. The service bulletin describes 
procedures for measuring the turnbuckle gap on the inflation cylinder 
of the off-wing emergency escape slides (to ensure it meets the maximum 
allowable spacing limit), and performing corrective actions if 
necessary. The corrective actions include crimping the gap to the 
correct spacing, making sure the turnbuckle can rotate around the 
cable; and replacing the adjustable bottle cable assembly with a new 
assembly if the turnbuckle cannot rotate.
    Special Attention Service Bulletin 767-25-0358 refers to Goodrich 
Service Bulletin 130104-25-342, dated July 23, 2003, as an additional 
source of service information.
    We have also reviewed Boeing Special Attention Service Bulletin 
767-25-0317, dated June 27, 2002. The service bulletin describes 
procedures for installing a safety device on the PFIM of the inflation 
cylinder of the off-wing emergency escape slide system and part-marking 
the inflation cylinder if applicable.
    Special Attention Service Bulletin 767-25-0317 refers to Goodrich 
Service Bulletin 130104-25-328, Revision 1, dated July 23, 2003, as an 
additional source of service information.
    Accomplishing the actions specified in the Boeing service 
information is intended to adequately address the unsafe condition.

FAA's Determination and Requirements of the Proposed AD

    We have evaluated all pertinent information and identified an 
unsafe condition that is likely to exist or develop on other airplanes 
of this same type design. Therefore, we are proposing this AD, which 
would require accomplishing the actions specified in the Boeing service 
information described previously, except as discussed under 
``Difference Between the Proposed AD and Boeing Service Information.''

Difference Between the Proposed AD and Boeing Service Information

    The service bulletins recommend that the actions therein be 
accomplished ``at the next normally scheduled maintenance period when 
manpower, materials, and facilities are available.'' We find that such 
a non-specific compliance time may not ensure that the proposed actions 
are accomplished in a timely manner. In developing an appropriate 
compliance time for these actions, we considered the safety 
implications, operators' normal maintenance schedules, and the 
compliance time recommended by the airplane manufacturer. In 
consideration of these items, we have determined that 18 months 
represents an appropriate interval of time wherein the proposed actions 
can be accomplished during scheduled maintenance intervals for the 
majority of affected operators, and an acceptable level of safety can 
be maintained. This compliance time is consistent with the 
recommendation of the airplane manufacturer.

Clarification of ``Concurrent'' Service Information

    The Boeing service bulletins specify concurrent accomplishment of 
the Goodrich service bulletins; however, this proposed AD refers to the 
Goodrich service bulletins as additional sources of service 
information.

Costs of Compliance

    There are about 696 airplanes of the affected design in the 
worldwide fleet. This proposed AD would affect about 297 airplanes of 
U.S. registry.
    The proposed inspection would take about 1 work hour per airplane, 
at an average labor rate of $65 per work hour. Based on these figures, 
the estimated cost of the proposed inspection for U.S. operators is 
$19,305, or $65 per airplane.
    The proposed safety device installation would take about 3 work 
hours per airplane, at an average labor rate of $65 per work hour. 
Required parts cost would be minimal. Based on these figures, the 
estimated cost of the proposed installation for U.S. operators is 
$57,915, or $195 per airplane.

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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 the proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the 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 proposed AD. 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, Safety.

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

    1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by adding the following new 
airworthiness directive (AD):

Boeing: Docket No. FAA-2005-21715; Directorate Identifier 2004-NM-
277-AD.

Comments Due Date

    (a) The Federal Aviation Administration (FAA) must receive 
comments on this AD action by August 22, 2005.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Boeing Model 767-200 and -300 series 
airplanes; certificated in any category; equipped with off-wing

[[Page 38823]]

emergency escape slides; as identified in Boeing Special Attention 
Service Bulletin 767-25-0358, dated September 18, 2003; and Boeing 
Special Attention Service Bulletin 767-25-0317, dated June 27, 2002.

Unsafe Condition

    (d) This AD was prompted by a report indicating that the 
inflation trigger cable may inadvertently disconnect from the 
inflation turnbuckle of the inflation cylinder of the off-wing 
emergency escape slide, due to incorrect spacing of the cable 
insertion gap; and additional reports indicating that the pull force 
increase mechanism (PFIM) on the off-wing charged cylinder 
assemblies of the escape slide may be inadvertently disengaged. We 
are issuing this AD to prevent failed deployment of the emergency 
escape slide during an emergency, which could impede an evacuation 
and result in injury to passengers or airplane crewmembers, or 
inadvertent inflation and loss of an emergency escape slide during 
flight, which could result in possible structural damage to 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.

Measurement/Corrective Action

    (f) Within 18 months after the effective date of this AD: 
Accomplish the actions specified in paragraphs (f)(1) and (f)(2) of 
this AD.
    (1) Measure the turnbuckle gap of the inflation cylinder of the 
off-wing emergency escape slides to ensure it meets the maximum 
allowable spacing limit and do applicable corrective actions by 
doing all the actions specified in the Accomplishment Instructions 
of Boeing Special Attention Service Bulletin 767-25-0358, dated 
September 18, 2003. Accomplish any corrective action before further 
flight in accordance with the service bulletin.
    (2) Install a safety device on the PFIM of the inflation 
cylinder of the off-wing emergency escape slides, and part-mark the 
inflation cylinder as applicable, by doing all the actions specified 
in the Accomplishment Instructions of Boeing Special Attention 
Service Bulletin 767-25-0317, dated June 27, 2002.

    Note 1: Goodrich Service Bulletins 130104-25-342, dated July 23, 
2003; and 130104-25-328, Revision 1, dated July 23, 2003; may be 
used as additional sources of service information for accomplishing 
the actions.

Parts Installation

    (g) As of the effective date of this AD, no person may install 
an inflation cylinder of the off-wing emergency escape slides on any 
airplane, unless it has been modified according to paragraph (f) of 
this AD.

Alternative Methods of Compliance (AMOCs)

    (h) The Manager, Seattle Aircraft Certification Office, FAA, has 
the authority to approve AMOCs for this AD, if requested in 
accordance with the procedures found in 14 CFR 39.19.

    Issued in Renton, Washington, on June 24, 2005.
Michael J. Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-13222 Filed 7-5-05; 8:45 am]
BILLING CODE 4910-13-P

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