AD 95-18-05

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AD Number:
95-18-05
Document Type:
AD Final Rules
Docket Number:
95-CE-52-AD
Subject Heading:
Airworthiness Directives; Fairchild Aircraft Models SA226-AT and SA226-TC Airplanes
Subject:
Aluminum Cargo Door Receptacles
Status:
Current
Citation:
Federal Register: September 15, 1995 (Volume 60, Number 179)
Citation Publish Date:
09/15/1995
Effective Date:
09/26/1995
Make:
M7 Aerospace LLC
Model:
SA226-AT | SA226-TC
Product Type:
Aircraft
Product Subtype:
Small/Large Airplane
Affected AD:
Superseded AD:
Affected By:
Superseded By:
Service/Office:
Office of Primary Responsibility:
CFR Part Reference:
Part 39 [60 FR 47862 NO. 179 9/15/95]
Comments:
AIRWORTHINESS DIRECTIVES FINAL RULES: 95-18-05
CITATION:   [Federal Register: September 15, 1995 (Volume 60, Number 179)]

PAGE NUMBER:   [Page 47862]

DOCKET NUMBER:   95-CE-52-AD

AMENDMENT:   39-9353

AD NUMBER:   95-18-05

SUBJECT HEADING:   Airworthiness Directives; Fairchild Aircraft Models SA226-AT and SA226-TC Airplanes

ACTION:   Final rule; request for comments.

SUMMARY:   This amendment adopts a new airworthiness directive (AD) that applies to certain Fairchild Aircraft Models SA226-AT and SA226-TC airplanes. This action requires replacing the two lower aluminum cargo door receptacles with steel receptacles. A report of cargo door failure on one of the affected airplanes prompted this action. Fatigue of the two bottom cargo door receptacles caused the bottom third of the cargo door to bend outward and upward, causing damage to the fuselage door frame. The actions specified by this AD are intended to prevent decompression injuries and the cargo door from breaking off and striking the empennage or the elevator, which could cause substantial structural failure and loss of control of the airplane.

DATES:   Effective September 26, 1995. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of September 26, 1995. Comments for inclusion in the Rules Docket must be received on or before October 26, 1995.

ADDRESSES:   Submit comments in triplicate to the Federal Aviation Administration (FAA), Central Region, Office of the Assistant Chief Counsel, Attention: Rules Docket 95-CE-52-AD, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106.

Service information that applies to this AD may be obtained from Fairchild Aircraft, P.O. Box 790490, San Antonio, Texas 78279-0490. This information may also be examined at the Federal Aviation Administration (FAA), Central Region, Office of the Assistant Chief Counsel, Attention: Rules Docket 95-CE-52-AD, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:   Hung Viet Nguyen, Aerospace Engineer, FAA, Aircraft Certification Office, 2601 Meacham Boulevard, Fort Worth, Texas 76193-0150; telephone (817) 222-5155; facsimile (817) 222-5960.

SUPPLEMENTARY INFORMATION:  
The FAA has received a report of failure of a cargo door on a Fairchild Aircraft SA226 series airplane while it was in flight. Fatigue of the two bottom cargo door receptacles caused the bottom third of the cargo door to bend outward and upward, causing damage to the fuselage door frame. This condition, if not detected and corrected, could result in the following:

decompression injuries as a result of the door being opened,

the door separating from the airplane, striking the empennage, and causing substantial structural failure, and

the door separating from the airplane, striking the elevator, and causing loss of control of the airplane.

Fairchild Service Bulletin (SB) 226-52-008; Issued: April 3, 1979; Revised: April 6, 1984, specifies procedures for replacing the two lower aluminum cargo door receptacles with steel receptacles.

After examining the circumstances and reviewing all available information related to the incidents described above, including the referenced service bulletin, the FAA has determined that AD action should be taken in order to prevent decompression injuries and the cargo door from breaking off and striking the empennage or the elevator, which could cause substantial structural failure and loss of control of the airplane.

Since an unsafe condition has been identified that is likely to exist or develop in other Fairchild Aircraft SA226 series airplanes of the same type design, this AD requires replacing the two lower aluminum cargo door receptacles with steel receptacles. The actions shall be accomplished in accordance with Fairchild SB 226-52-008; Issued: April 3, 1979, Revised: April 6, 1984. In future rulemaking actions, the FAA may impose life limits on the cargo door and require additional cargo door modifications.

Since a situation exists (possible decompression and empennage or elevator failure) that requires the immediate adoption of this regulation, it is found that notice and opportunity for public prior comment hereon are impracticable, and that good cause exists for making this amendment effective in less than 30 days.

Comments Invited
Although this action is in the form of a final rule that involves requirements affecting immediate flight safety and, thus, was not preceded by notice and opportunity to comment, comments are invited on this rule. Interested persons are invited to comment on this rule by submitting such written data, views, or arguments as they may desire. Communications should identify the Rules Docket number and be submitted in triplicate to the address specified above. All communications received on or before the closing date for comments will be considered, and this rule may be amended in light of the comments received. Factual information that supports the commenter's ideas and suggestions is extremely helpful in evaluating the effectiveness of the AD action and determining whether additional rulemaking action would be needed.

Comments are specifically invited on the overall regulatory, economic, environmental, and energy aspects of the rule that might suggest a need to modify the rule. All comments submitted will be available, both before and after the closing date for comments, in the Rules Docket for examination by interested persons. A report that summarizes each FAA-public contact concerned with the substance of this AD will be filed in the Rules Docket.

Commenters wishing the FAA to acknowledge receipt of their comments submitted in response to this notice must submit a self-addressed, stamped postcard on which the following statement is made: "Comments to Docket No. 95-CE-52-AD." The postcard will be date stamped and returned to the commenter.

The regulations adopted herein will not have substantial direct effects 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. Therefore, in accordance with Executive Order 12612, it is determined that this final rule does not have sufficient federalism implications to warrant the preparation of a Federalism Assessment.

The FAA has determined that this regulation is an emergency regulation and that must be issued immediately to correct an unsafe condition in aircraft, and is not a "significant regulatory action" under Executive Order 12866. It has been determined further that this action involves an emergency regulation under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979). If it is determined that this emergency regulation otherwise would be significant under DOT Regulatory Policies and Procedures, a final regulatory evaluation will be prepared and placed in the Rules Docket (otherwise, an evaluation is not required). A copy of it, if filed, may be obtained from the Rules Docket.

List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.

Adoption of the Amendment
Accordingly, pursuant to 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
1. The authority citation for part 39 continues to read as follows:
Authority: 49 USC 106(g), 40101, 40113, 44701.

Section 39.13 - [AMENDED]
2. Section 39.13 is amended by adding a new airworthiness directive (AD) to read as follows:

REGULATORY TEXT:  
95-18-05 FAIRCHILD AIRCRAFT CORPORATION: Amendment 39-9353; Docket No. 95-CE-52-AD.

Applicability: Models SA226-AT (serial numbers AT001 through AT074) and SA226-TC (serial numbers TC201 through TC419) airplanes, certificated in any category.

NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must use the authority provided in paragraph (c) of this AD to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition, or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any airplane from the applicability of this AD.

Compliance: Required within the next 50 hours time-in-service after the effective date of this AD, unless already accomplished.

To prevent decompression injuries and the cargo door from breaking off and striking the empennage or the elevator, which could cause substantial structural failure and loss of control of the airplane, accomplish the following:

(a) Replace the lower two aluminum cargo door receptacles with steel receptacles in accordance with the ACCOMPLISHMENT INSTRUCTIONS section of Fairchild Aircraft Service Bulletin (SB) 226-52-008; Issued: April 3, 1979; Revised: April 6, 1984.

(b) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished.

(c) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, FAA, Aircraft Certification Office, 2601 Meacham Boulevard, Fort Worth, Texas 76193-0150. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Fort Worth Aircraft Certification Office.

NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Fort Worth Aircraft Certification Office.

(d) The replacements required by this AD shall be done in accordance with Fairchild Aircraft Service Bulletin 226-52-008; Issued April 3, 1979; Revised April 6, 1984. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Fairchild Aircraft, P.O. Box 790490, San Antonio, Texas 78279-0490. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 800 North Capitol Street, NW., 7th Floor, suite 700, Washington, DC.

(e) This amendment becomes effective on September 26, 1995.

FOOTER: