Source: https://www.scribd.com/document/2753113/Rule-Airworthiness-directives-Cessna-Aircraft-Company-Models-525-525A-and-525B-Airplanes
Timestamp: 2018-02-24 03:31:46
Document Index: 581910036

Matched Legal Cases: ['art 39', 'art 39', 'art 39', 'art 39', 'art 39', 'ART 39', '§ 39', 'art 51']

Rule: Airworthiness directives: Cessna Aircraft Company Models 525, 525A, and 525B Airplanes | Federal Aviation Administration | Airplane
Description: Rule: Airworthiness directives: Cessna Aircraft Company Models 525, 525A, and 525B Airplanes, 6582-6584 [E8-1821] Federal Aviation Administration
Rule: Airworthiness directives: Cessna Aircraft Company Models 525, 525A, and 525B Airplanes, 6582-6584 [E8-1821] Federal Aviation Administration
Federal Register / Vol. 73, No. 24 / Tuesday, February 5, 2008 / Rules and Regulations
fuselage fairings before reinstalling; and disable the cockpit mounted pilot relief tube. This AD results from leaking of the cockpit mounted pilot relief tube, which caused corrosion of the airplane structure. We are issuing this AD to detect and correct any damage from corrosion of the airplane structure. Corrosion of the airplane structure could cause structural degradation and lead to structural failure of the airplane with consequent loss of control. DATES: This AD becomes effective on March 11, 2008. On March 11, 2008, the Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD. ADDRESSES: For service information identified in this AD, contact Cessna Aircraft Company, Citation Marketing Division, P.O. Box 7706, Wichita, Kansas 67277; telephone: 1–800–835– 4090; fax: 1–800–517–8500. To view the AD docket, go to U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, or on the Internet at http:// www.regulations.gov. The docket number is FAA–2007–28956; Directorate Identifier 2007–CE–068–AD. FOR FURTHER INFORMATION CONTACT: T.N. Baktha, Aerospace Engineer,1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946– 4155; fax: (316) 946–4107. SUPPLEMENTARY INFORMATION: Discussion On October 22, 2007, we issued a proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to
Parts cost Not applicable ..................................
or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on January 24, 2008. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8–1813 Filed 2–4–08; 8:45 am]
[Docket No. FAA–2007–28956; Directorate Identifier 2007–CE–068–AD; Amendment 39–15360; AD 2008–03–10] RIN 2120–AA64
include an AD that would apply to certain Cessna Models 525, 525A, and 525B airplanes. This proposal was published in the Federal Register as a notice of proposed rulemaking (NPRM) on October 26, 2007 (72 FR 60790). The NPRM proposed to require you to inspect the lower wing skin structure, forward wing spar, lower fuselage skin, fairings, and the external fairing frames for corrosion; repair any damage found; apply a corrosion inhibitive sealant to the fuselage fairings before reinstalling; and disable the cockpit mounted pilot relief tube. Comments We provided the public the opportunity to participate in developing this AD. We received no comments on the proposal 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 except for minor editorial corrections. We have determined that these minor corrections: • Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. Costs of Compliance We estimate that this AD affects 261 airplanes in the U.S. registry. We estimate the following costs to do the inspection:
Total cost per airplane $6,400 Total cost on U.S. operators $1,670,400
Airworthiness Directives; Cessna Aircraft Company Models 525, 525A, and 525B Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule.
AGENCY: SUMMARY: We are adopting a new airworthiness directive (AD) for certain Cessna Aircraft Company (Cessna) Models 525, 525A, and 525B airplanes. This AD requires you to inspect the lower wing skin structure, forward wing spar, lower fuselage skin, fairings, and the external fairing frames for corrosion; repair any damage found; apply a corrosion inhibitive sealant to the
Labor cost 80 work-hours × $80 per hour = $6,400 ...................................................
We have no way of determining the number of airplanes that may need repair or further inspection based on the
results of the inspection, or the costs associated with such repair or inspection.
We estimate the following costs to disable the cockpit mounted pilot relief tube:
Total cost per airplane $40 Total cost on U.S. operators $10,440
.5 work-hour × $80 per hour = $40 ...........................................................
Not applicable ..................................
Cessna will provide warranty credit to the extent specified in Cessna Citation Service Bulletin SB525–53–20, dated April 30, 2007; Cessna Citation Service Bulletin SB525A–53–01, dated April 30, 2007; Cessna Citation Service Bulletin SB525B–53–01, dated April 30, 2007; Cessna Citation Alert Service Letter
ASL525–53–04, Revision 2, dated August 19, 2007; Cessna Citation Alert Service Letter ASL525A–53–05, Revision 2, dated July 25, 2007; and Cessna Citation Alert Service Letter ASL525B–53–02, Revision 2, dated July 25, 2007.
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
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05FER1
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 AD. 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 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 summary of the costs to comply with this AD (and other information as included in the Regulatory Evaluation) and placed it in the AD Docket. You may get a copy of this summary by sending a request to us at the address listed under ADDRESSES. Include ‘‘Docket No. FAA–2007–28956; Directorate Identifier 2007-CE–068-AD’’ in your request. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment
2008–03–10 Cessna Aircraft Company: Amendment 39–15360; Docket No. FAA–2007–28956; Directorate Identifier 2007-CE–068-AD. Effective Date (a) This AD becomes effective on March 11, 2008. Affected ADs (b) None. Applicability (c) This AD applies to the following airplane models and serial numbers that have a cockpit mounted pilot relief tube installed and are certificated in any category: Models (1) 525 .......................... (2) 525A ....................... (3) 525B ....................... Unsafe Condition (d) This AD results from leaking of the pilot relief tube, which caused corrosion of the airplane structure. We are issuing this AD to detect and correct any damage from corrosion on the airplane structure. Corrosion of the airplane structure could cause structural degradation and lead to structural failure of the airplane with consequent loss of control. Compliance (e) To address this problem, you must do the following, unless already done: Serial No. 0001 through 0637. 0001 through 0347. 0001 through 0152.
Accordingly, under the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: PART 39—AIRWORTHINESS DIRECTIVES
2. FAA amends § 39.13 by adding the following new AD:
Actions (1) Inspect the lower wing skin structure, forward wing spars, lower fuselage skin, fairings, and external fairing frames for corrosion. Compliance Within the next 90 days after March 11, 2008 (the effective date of this AD). Procedures Follow Cessna Citation Alert Service Letter ASL525–53–04, Revision 2, dated August 19, 2007; Cessna Citation Alert Service Letter ASL525A–53–05, Revision 2, dated July 25, 2007; or Cessna Citation Alert Service Letter ASL525B–53–02, Revision 2, dated July 25, 2007. Follow Cessna Citation Alert Service Letter ASL525–53–04, Revision 2, dated August 19, 2007; Cessna Citation Alert Service Letter ASL525A–53–05, Revision 2, dated July 25, 2007; or Cessna Citation Alert Service Letter ASL525B–53–02, Revision 2, dated July 25, 2007.
(2) If corrosion damage is found in the lower wing skin structure, forward wing spars, lower fuselage skin, fairings, or external fairing frames during the inspection required in paragraph (e)(1) of this AD, repair as specified in the applicable service information. If the corrosion damage cannot be repaired within the limits specified in the applicable service information, contact the manufacturer at 1–800–835–4090 for an FAA-approved repair scheme and incorporate this repair. (3) If corrosion on the lower wing skin structure, forward wing spars, and lower fuselage skin was repaired by blending within the limits specified in the service information, do a surface eddy current inspection or a dyepenetrant inspection for cracks.
Before further flight after the inspection required in paragraph (e)(1) of this AD.
Before further flight after the repair by blending was done as specified in paragraph (e)(2) of this AD.
(4) If cracks are found during the surface eddy current inspection or the dye-penetrant inspection required in paragraph (e)(3) of this AD, contact the manufacturer for an FAA-approved repair scheme and incorporate this repair.
Before further flight after the inspection required in paragraph (e)(3) of this AD.
Follow Cessna Citation Alert Service Letter ASL525–53–04, Revision 2, dated August 19, 2007; Cessna Citation Alert Service Letter ASL525A–53–05, Revision 2, dated July 25, 2007; or Cessna Citation Alert Service Letter ASL525B–53–02, Revision 2, dated July 25, 2007. Contact Cessna Aircraft Company, Citation Customer Support at 1–800–835–4090.
Federal Register / Vol. 73, No. 24 / Tuesday, February 5, 2008 / Rules and Regulations TABLE 1.—ACTIONS, COMPLIANCE, AND PROCEDURES—Continued
Actions Compliance Before further flight after the inspection required in paragraph (e)(1) of this AD if no corrosion was found; or before further flight after doing the repairs and inspections required in paragraphs (e)(2), (e)(3), and (e)(4) of this AD if corrosion or cracks were found. Before further flight after the inspection required in paragraph (e)(1) of this AD. Procedures Follow Cessna Citation Alert Service Letter ASL525–53–04, Revision 2, dated August 19, 2007; Cessna Citation Alert Service Letter ASL525A–53–05, Revision 2, dated July 25, 2007; or Cessna Citation Alert Service Letter ASL525B–53–02, Revision 2, dated July 25, 2007. Cessna Citation Service Bulletin SB525–53– 20, dated April 30, 2007; Cessna Citation Service Bulletin SB525A–53–01, dated April 30, 2007; or Cessna Citation Service Bulletin SB525B–53–01, dated April 30, 2007.
(5) Install the fuselage fairings and apply corrosion inhibitive sealant.
(6) Determine the type of installation of the cockpit mounted pilot relief tube and disable the relief tube.
Alternative Methods of Compliance (AMOCs) (f) The Manager, Wichita Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: T.N. Baktha, Wichita ACO, Aerospace Engineer, 1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946–4155; fax: (316) 946–4107. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight
Standards District Office (FSDO), or lacking a PI, your local FSDO. Material Incorporated by Reference (g) You must use the service information specified in Table 2 of this AD to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Cessna Aircraft Company,
Citation Marketing Division, P.O. 7706, Wichita, Kansas 67277; telephone: 1–800– 835–4090; fax: 1–800–517–8500. (3) You may review copies at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Kansas City, Missouri 64106; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html.
Service Bulletin No. Cessna Cessna Cessna Cessna Cessna Cessna Citation Citation Citation Citation Citation Citation Alert Service Letter ASL525–53–04 ..................................................................................... Alert Service Letter ASL525A–53–05 ................................................................................... Alert Service Letter ASL525B–53–02 ................................................................................... Service Bulletin SB525A–53–20 ........................................................................................... Service Bulletin SB525A–53–01 ........................................................................................... Service Bulletin SB525B–53–01 ........................................................................................... Revision 2 2 2 .................... .................... .................... Date August 19, 2007. July 25, 2007. July 25, 2007. April 30, 2007 April 30, 2007. April 30, 2007.
Issued in Kansas City, Missouri, on January 24, 2008. John Colomy, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E8–1821 Filed 2–4–08; 8:45 am]
[Docket No. FAA–2008–0100; Directorate Identifier 2007–SW–41–AD; Amendment 39– 15356; AD 2008–03–07] RIN 2120–AA64
SUMMARY: We are adopting a new airworthiness directive (AD) for Eurocopter Model AS 332 L2 helicopters. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority to identify and correct an unsafe condition on an aviation product. The European Aviation Safety Agency (EASA), the Technical Agent of France, with which we have a bilateral agreement, states in the MCAI:
result in a drop of internal pressure of the cylinder. This internal damage, if not corrected, could lead to functional failure of the cylinder, making the life raft inflation no longer possible.
This AD requires actions that are intended to address the failure of a life raft to inflate during an emergency landing on water (ditching), which could result in loss of the crew and passengers. This AD becomes effective on February 20, 2008. The Director of the Federal Register approved the incorporation by reference of Eurocopter Alert Service Bulletin No. 05.00.71, dated July 31, 2007, as of February 20, 2008. We must receive comments on this AD by April 7, 2008. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251.
A borescope inspection during scheduled maintenance revealed wear on the internal skin of a Life Raft Inflation Cylinder, P/N 41918001, that had been installed on a Eurocopter AS 332 L2 helicopter. The plunger tube end is fitted with a metal endfitting that presses against the internal surface of the cylinder due to its installation horizontally aboard the aircraft. Vibrations generated by helicopter operation are therefore causing such wear, which may
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