RULES and REGULATIONS

DEPARTMENT OF TRANSPORTATIONc

14 CFR Part 39

[Docket No. 90-NM-217-AD; Amdt. 39-7032; AD 91-13-01]

Airworthiness Directives; Airbus Industrie Model A310-200 Series Airplanes

Monday, June 10, 1991

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Industrie 

Model A310-200 series airplanes, which requires repetitive visual inspections to detect cracks in a certain frame 

reinforcement angle runout; and repair, if necessary. This amendment also provides for terminating action for the 

repetitive inspections. This amendment is prompted by full scale fatigue testing by the manufacturer which revealed 

cracks in Frame 46 between Stringer 21 and Stringer 22. This condition, if not corrected, could result in reduced 

structural integrity of the fuselage.

EFFECTIVE DATE: July 15, 1991.

ADDRESSES: The applicable service information may be obtained from Airbus Industrie, Airbus Support Division, 

Avenue Didier Daurat, 31700 Blagnac, France. This information may be examined at the FAA, Northwest Mountain 

Region, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington.

FOR FURTHER INFORMATION CONTACT: Mr. Greg Holt, Standardization Branch, ANM-113; telephone (206) 

227-2140. Mailing address: FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue 

SW., Renton, Washington 98055-4056.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal Aviation Regulations to include 

a new airworthiness directive, applicable to certain Airbus Industrie Model A310-200 series airplanes, which requires repetitive visual inspections to detect cracks in a certain frame reinforcement angle runout; repair, if necessary; and reinforcement of the angle runout; was published in the Federal Register on December 20, 1990 (55 FR 

52177).

Interested persons have been afforded an opportunity to participate in the making of this amendment. Due consideration has been given to the comments received.

One commenter noted that the applicability statement of the AD should apply to Model A310-200 series airplanes 

with serial numbers 162 through 357, inclusive, since the first manufacturer's serial number was 162. The FAA concurs. The applicability statement has been changed accordingly.

Two commenters objected to mandating the modification addressed in Airbus Industrie Service Bulletin A310-53-

2019, and suggested that the proposed requirement to install the modification be deleted. The commenters stated that 

the inspections specified in Service Bulletin A310-53-2054 are adequate to ensure the continued structural airworthiness of the airplanes. Furthermore, the commenters stated that cracking had occurred only during fatigue testing
and has not occurred on in-service airplanes. The commenters further noted that milling required to accomplish the 

modification has a very high risk factor; and that there would be a high probability that the reinforcement angle 

runout would be damaged and would require extensive repair or replacement. One of these commenters, Airbus Industrie, stated that, in view of the ease of inspecting this area, any damage that might occur would be easily detected. The FAA concurs. Upon further review of the proposed inspection criteria and interval, the FAA has determined 

that the structural integrity of the airplane can be assured with the continued inspection of the frame reinforcement 

angle runout because (1) the inspections are easily performed, (2) the area is easily accessible, and (3) the required 

inspections will likely detect damage in a timely manner, before failure could occur. Therefore, the final rule has 

been revised to delete the modification requirement. The final rule continues to provide for the optional modification 

of the reinforcement angle runout by tapering the angle and reducing the thickness; once this is accomplished, the 

required repetitive inspections may be terminated.

The economic analysis paragraph below has been revised to reflect only the cost for the repetitive inspections. Since 

the proposed mandatory modification requirement has been deleted from the final rule, related parts cost have also 

been deleted from the economic analysis.

The economic analysis paragraph has also been revised to increase the specified hourly labor rate from $40 per 

manhour (as was cited in the preamble to the Notice) to $55 per manhour. The FAA has determined that it is necessary to increase this rate used in calculating the cost impact associated with AD activity to account for various inflationary costs in the airline industry.

Paragraph C. of the final rule has been revised to specify the current procedure for submitting requests for approval 

of alternative methods compliance.

After careful review of the available data, including the comment noted above, the FAA has determined that air 

safety and the public interest require the adoption of the rule with the changes noted above. These changes will neither significantly increase the economic burden on affected operators nor increase the scope of the final rule.

It is estimated that 7 airplanes of U.S. registry will be affected by this AD, that it will take approximately 22 manhours per airplane to accomplish the required actions, and that the average labor cost will be $55 per manhour. 

Based on these figures, the total cost impact of the AD on U.S. operators is estimated to be $8,470.

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.

For the reasons discussed above, I certify that this action: (1) Is not a “major rule” under Executive Order 12291; (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. A final evaluation has been prepared for this action and is contained in the 

Rules Docket. A copy of it may be obtained from the Rules Docket.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Safety.

Adoption of the Amendment

Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration 

amends 14 CFR part 39 of the Federal Aviation Regulations as follows:
PART 39—[AMENDED]1. The authority citation for part 39 continues to read as follows:

Authority: 49 U.S.C. 1354(a), 1421 and 1423; 49 U.S.C. 106(g) (Revised Pub. L. 97-449, January 12, 1983); and 14 

CFR 11.89.

§ 39.13 [Amended]

14 CFR § 39.13

2. Section 39.13 is amended by adding the following new airworthiness directive:

91-13-01. Airbus Industrie: Amendment 39-7032. Docket No. 90-NM-217-AD.

Applicability: Model A310-200 series airplanes, Serial Numbers 162 through 357, certificated in any category.

Compliance: Required as indicated, unless previously accomplished.

To prevent reduced structural integrity of the fuselage, accomplish the following:

A. Prior to the accumulation of 12,000 landings, or within 2,000 landings after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 3,000 landings, perform a visual inspection of Frame 46 at 

the level of the frame reinforcement angle runout between Stringer 21 and Stringer 22 (left and right), in accordance 

with Airbus Industrie Service Bulletin A310-53-2054, Revision 2, dated May 22, 1990. If cracks are found, prior to 

further flight, repair in accordance with the service bulletin.

B. Modification of the reinforcement angle runout by tapering the angle and reducing the thickness, in accordance 

with Airbus Industrie Service Bulletin A310-53-2019, Revision 2, dated May 22, 1990, constitutes terminating action for the repetitive inspections required by paragraph A. of this AD.

C. An alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of 

safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane 

Directorate.

Note: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113.

D. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in 

order to comply with the requirements of this AD.

All persons affected by this directive who have not already received the appropriate service documents from the 

manufacturer may obtain copies upon request to Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 

31700 Blagnac, France. These documents may be examined at the FAA, Northwest Mountain Region, Transport 

Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington.
This amendment (39-7032 , AD 91-13-01 ) becomes effective July 15, 1991.

Issued in Renton, Washington, on May 30, 1991.

Darrell M. Pederson,

Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 91-13647 Filed 6-7-91; 8:45 am]

56 FR 26602-01