This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

the Superintendent of Documents. Prices of

new books are listed in the first FEDERAL

REGISTER issue of each week.

Rules and Regulations Federal Register

53847

Vol. 60, No. 201

Wednesday, October 18, 1995

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 94–NM–243–AD; Amendment

39–9395; AD 95–21–09]

Airworthiness Directives; Airbus Model

A300 and A300–600 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to all Airbus Model A300

series airplanes, that currently requires

repetitive inspections for cracking of the

No. 2 flap beams, and replacement of

the flap beams, if necessary. That AD

was prompted by reports of cracking of

the No. 2 flap beams. This amendment

provides optional modifications for

extending certain inspection thresholds,

and an optional terminating

modification for certain inspections.

This amendment also expands the

applicability of the existing AD to

include Model A300–600 series

airplanes. The actions specified by this

AD are intended to prevent asymmetry

of the flaps due to cracking of the No.

2 flap beams.

DATES: Effective November 17, 1995.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of November

17, 1995.

ADDRESSES: The service information

referenced in this AD may be obtained

from Airbus Industrie, 1 Rond Point

Maurice Bellonte, 31707 Blagnac Cedex,

France. This information may be

examined at the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, Rules Docket,

1601 Lind Avenue, SW., Renton,

Washington; or at the Office of the

Federal Register, 800 North Capitol

Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Tim

Backman, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–2797; fax (206) 227–1149.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39)

by superseding AD 85–07–04,

amendment 39–5027 (49 FR 45755,

April 2, 1985), which is applicable to all

Airbus Model A300 series airplanes,

was published in the Federal Register

on June 9, 1995 (60 FR 30471). That

action proposed to continue to require

repetitive inspections for cracking of the

No. 2 flap beams of Model A300 series

airplanes, and replacement of the flap

beams, if necessary. That action also

proposed to require identical

inspections of Model A300–600 series

airplanes. Additionally, that action

proposed to provide an optional

terminating modification for the

repetitive inspections on the Model

300–600 series airplanes, and optional

modifications for extending certain

inspection thresholds for Model A300

series airplanes.

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 supports the

proposed rule.

Another commenter also supports the

proposed rule, but points out that

paragraph (d)(3) of the proposed AD

contains a typographical error.

Paragraph (d)(3) should read ‘‘perform

the ultrasonic inspection required by

paragraph (d) of this AD.’’ Paragraph

(d)(3) currently references paragraph (b).

The FAA acknowledges a typographical

error, and has revised paragraph (d)(3)

of the final rule accordingly.

After careful review of the available

data, including the comments noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule with the change

previously described. The FAA has

determined that this change will neither

increase the economic burden on any

operator nor increase the scope of the

AD.

There are approximately 23 Model

A300 series airplanes and 45 Model

A300–600 series airplanes of U.S.

registry that will be affected by this AD.

The inspections that are currently

required by AD 85–07–04, and

applicable to the Model A300 series

airplanes, take approximately 6 work

hours per airplane, per inspection cycle,

to accomplish at an average labor rate of

$60 per work hour. Based on these

figures, the total cost impact of the

actions required by AD 85–07–04 on

U.S. operators of these airplanes is

estimated to be $8,280, or $360 per

airplane, per inspection cycle.

The inspections that are required by

this new AD, and applicable to Model

A300–600 series airplanes will take

approximately 6 work hours per

airplane to accomplish, at an average

labor rate of $60 per work hour. Based

on these figures, the total cost impact of

these new requirements on U.S.

operators of these airplane is estimated

to be $16,200, or $360, per airplane, per

inspection cycle.

The total cost impact figures

discussed above are based on

assumptions that no operator has yet

accomplished any of the requirements

of this AD action, and that no operator

would accomplish those actions in the

future if this AD were not adopted.

Should an operator of a Model A300–

600 series airplane elect to accomplish

the optional terminating action rather

than continue the repetitive inspections,

it would take approximately 55 work

hours to accomplish it, at an average

labor ate of $60 per work hour. Based

on these figures, the total cost impact of

this optional terminating action would

be $3,300 per airplane.

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

‘‘significant regulatory action’’ under

Executive Order 12866; (2) is not a

‘‘significant rule’’ under DOT

Regulatory Policies and Procedures (44
53848 Federal Register / Vol. 60, No. 201 / Wednesday, October 18, 1995 / Rules and Regulations

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 it is

contained in the Rules Docket. A copy

of it may be obtained from the Rules

Docket at the location provided under

the caption ADDRESSES.

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.

§ 39.13 [Amended]

2. Section 39.13 is amended by

removing amendment 39–5027 (49 FR

45755, April 2, 1985), and by adding a

new airworthiness directive (AD),

amendment 39–9395, to read as follows:

95–21–09 Airbus Industrie: Amendment

39–9395. Docket 94–NM–243–AD.

Supersedes AD 85–07–04, Amendment

39–5027.

Applicability: All Model A300 and A300–

600 series 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 (f) 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 as indicated, unless

accomplished previously.

To prevent asymmetry of the No. 2 flaps,

accomplish the following:

Note 2: Paragraph (a) of this AD restates the

requirement for an initial and repetitive

inspections contained in paragraph A. of AD

85–07–04. Therefore, for operators who have

previously accomplished at least the initial

inspection in accordance with AD 85–07–04,

paragraph (a) of this AD requires that the

next scheduled inspection be performed

within the intervals specified in (a)(1), (a)(2),

or (a)(3), as applicable, after the last

inspection performed in accordance with

paragraph A. of AD 85–07–04.

Note 3: Measurement of crack length is

performed by measurement of the probe

displacement (perpendicular to symmetry

plane of beam) between defect indication

appearance and its complete disappearance.

The bolt hole indication should not be

interpreted as an indication of a defect. These

two indications appear very close together

because the defects originate from the bolt

holes.

(a) For Model A300 series airplanes: Prior

to the accumulation of 15,000 total landings,

or within the next 120 days after May 9, 1985

(the effective date of AD 85–07–04,

amendment 39–5027), whichever occurs

later, inspect for cracking of the base steel

member and light alloy side members of the

No. 2 flap beams, left hand and right hand,

in accordance with the Accomplishment

Instructions of Airbus Service Bulletin A300–

57–116, Revision 6, dated July 16, 1993.

Note 4: Inspections required by paragraph

(a) of this AD that have been accomplished

prior to the effective date of this AD in

accordance with Airbus Service Bulletin

A300–57–116, Revision 1, dated August 27,

1983; Revision 2, dated April 24, 1984;

Revision 3, dated July 20, 1984; Revision 4,

dated August 13, 1986; or Revision 5, dated

July 10, 1989; as applicable; are considered

acceptable for compliance with the

applicable action specified in this

amendment.

(1) If no cracking is detected: Except as

provided by paragraph (c) of this AD, repeat

the inspection at intervals not to exceed

1,700 landings until the requirements of

paragraph (b) of this AD are accomplished.

(2) If any crack is detected that is less than

or equal to 4 mm: Repeat the inspection at

intervals not to exceed 250 landings, until

the requirements of paragraph (b) of this AD

are accomplished.

(3) If any crack is detected that exceeds 4

mm: Prior to further flight, replace the flap

beam in accordance with the service bulletin,

and prior to the accumulation of 15,000 flight

cycles on the replaced flap beam, perform the

ultrasonic inspection as required by

paragraph (b) of this AD.

(b) For Model A300 series airplanes: Prior

to the accumulation of 15,000 total landings,

or within the next 1,000 landings after the

effective date of this AD, whichever occurs

later, perform an ultrasonic inspection to

detect cracking of the No. 2 flap beams, in

accordance with Airbus Service Bulletin No.

A300–57–116, Revision 6, dated July 16,

1993. Accomplishment of this inspection

terminates the inspection required by

paragraph (a) of this AD.

(1) If no cracking is detected: Except as

provided by paragraph (c) of this AD, repeat

the ultrasonic inspections thereafter at

intervals not to exceed 1,700 landings.

(2) If any crack is detected beyond the bolt

hole, and that crack is less than or equal to

4 mm in length: Repeat the ultrasonic

inspections thereafter at intervals not to

exceed 250 landings.

(3) If any crack is detected beyond the bolt

hole and that crack is greater than 4 mm in

length: Prior to further flight, replace the flap

beam in accordance with the service bulletin,

and prior to the accumulation of 15,000 flight

cycles on the replaced flap beam, perform the

ultrasonic inspection as required by this

paragraph.

(c) For Model A300 series airplanes: After

accomplishing the initial inspection required

by paragraph (b) of this AD, accomplishment

of either paragraph (c)(1) or (c)(2) of this AD

extends the fatigue life of the No. 2 flap track

beam as specified in those paragraphs,

provided that no cracking is detected during

any inspection required by paragraph (a) or

(b) of this AD.

(1) Removal of any damage and the

installation of larger diameter bolts on the

No. 2 flap track beam (Modification No.

4740), in accordance with Airbus Service

Bulletin No. A300–57–128, Revision 3, dated

January 26, 1990, extends the interval for the

first repetitive inspection required by

paragraph (b) of this AD from 1,700 landings

to 12,000 landings, provided that

Modification No. 4740 is accomplished prior

to the accumulation of 16,700 total landings

on the flap beams. Following

accomplishment of the first repetitive

inspection, subsequent repetitive inspections

shall be performed at intervals not to exceed

1,700 landings. Or

(2) Cold working of the bolt holes and the

installation of larger diameter bolts on the

No. 2 flap track beam (Modification No.

5815), in accordance with Airbus Service

Bulletin No. A300–57–141, Revision 7, dated

July 16, 1993, extends the interval for the

first repetitive inspection required by

paragraph (b) of this AD from 1,700 landings

to the interval specified in paragraph (c)(2)(i)

or (c)(2)(ii) of this AD.

(i) If interference fit bolts that are 15/32-

inch in diameter are fitted, the interval for

the first repetitive inspection required by

paragraph (b) of this AD is extended to

22,000 landings, provided that Modification

5815 is accomplished prior to the

accumulation of 16,700 total landings on the

flap beam. Following accomplishment of the

first repetitive inspection required by

paragraph (b) of this AD, subsequent

repetitive inspections shall be performed at

intervals not to exceed 1,700 landings. Or

(ii) If interference fit bolts that are 7/16- or

3/8-inch in diameter are fitted, the interval

for the first repetitive inspection required by

paragraph (b) of this AD is extended to

33,000 landings, provided that Modification

5815 is accomplished prior to the

accumulation of 16,700 total landings on the

flap beam. Following accomplishment of the

first repetitive inspection required by

paragraph (b) of this AD, subsequent

repetitive inspections shall be performed at

intervals not to exceed 1,700 landings.

(d) For Model A300–600 series airplanes:

Prior to the accumulation of 15,000 total
Federal Register / Vol. 60, No. 201 / Wednesday, October 18, 1995 / Rules and Regulations 53849

landings, or within the next 1,000 landings

after the effective date of this AD, whichever

occurs later, perform an ultrasonic inspection

to detect cracking of the No. 2 flap track

beams, in accordance with Airbus Service

Bulletin No. A300–57–6005, Revision 2,

dated December 16, 1993.

(1) If no cracking is detected, repeat the

ultrasonic inspections thereafter at intervals

not to exceed 1,700 landings.

(2) If any crack is detected beyond the bolt

hole and that crack is less than or equal to

4 mm in length: Repeat the ultrasonic

inspections thereafter at intervals not to

exceed 250 landings.

(3) If any crack is detected beyond the bolt

hole and that crack is greater than 4 mm in

length: Prior to further flight, replace the flap

beam in accordance with the service bulletin,

and prior to the accumulation of 15,000

landings on the replaced flap beam, perform

the ultrasonic inspection required by

paragraph (d) of this AD.

(e) For Model A300–600 series airplanes:

Installation of oversized transition fit bolts in

cold-worked holes, in accordance with

Airbus Service Bulletin No. A300–57–6006

(Modification 5815), Revision 4, dated July

25, 1994, constitutes terminating action for

the repetitive inspection requirements of

paragraph (d) of this AD, provided that no

cracking is detected during any inspection

required by paragraph (d) of this AD, and

provided that the installation is

accomplished prior to the accumulation of

15,000 total landings. If any bolt requires

oversizing above 7/16-inch diameter during

accomplishment of this installation, prior to

further flight, repair in accordance with a

method approved by the Manager,

Standardization Branch, ANM–113, FAA,

Transport Airplane Directorate.

Note 5: If Airbus Service Bulletin No.

A300–57–6005, Revision 2, dated December

16, 1993, is accomplished concurrently with

Airbus Service Bulletin No. A300–57–6006 ,

Revision 3, dated December 16, 1993

(Modification 5815), the ultrasonic

inspection for cracking required by paragraph

(d) of this AD need not be performed since

the eddy current inspection detailed for

Modification 5815 is more comprehensive.

(f) An alternative method of compliance or

adjustment of the compliance time that

provides an acceptable level of safety may be

used if approved by the Manager,

Standardization Branch, ANM–113.

Operators shall submit their requests through

an appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, Standardization

Branch, ANM–113.

Note 6: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Standardization Branch,

ANM–113.

(g) 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.

(h) The actions shall be done in accordance

with the following Airbus service bulletins,

which contain the specified list of effective

pages:

Service bulletin referenced and date Page No. Revision level

shown on page

Date shown on

page

A300–57–116, Revision 6, July 16, 1993 .......................................................................... 1–11 6 July 16, 1993.

A300–57–128, Revision 3, January 26, 1990 ................................................................... 1 3 January 26,

1990.

2–5 1 February 7,

1986.

6–14 Original August 27,

1983.

A300–57–141, Revision 7, July 16, 1993 .......................................................................... 1–24 7 July 16, 1993.

A300–57–6005, Revision 2, December 16, 1993 .............................................................. 1–4 2 December 16,

1993.

5–7, 9 1 February 26,

1993.

8 Original August 13,

1986.

A300–57–6006, Revision 4, July 25, 1994 ........................................................................ 1, 2, 5, 7 4 July 25, 1994.

3, 4, 6, 8–20 3 December 16,

1993.

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 Airbus Industrie, 1 Rond Point Maurice

Bellonte, 31707 Blagnac Cedex, France.

Copies may be inspected at the FAA,

Transport Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington; or at the

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

(i) This amendment becomes effective on

November 17, 1995.

Issued in Renton, Washington, on October

3, 1995.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 95–25029 Filed 10–17–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 95–NM–174–AD; Amendment

39–9391; AD 95–21–06]

Airworthiness Directives; Airbus Model

A330 and A340 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Airbus Model

A330 and A340 series airplanes. This

action requires replacement of the fire

extinguisher distribution pipe and

attachments in the lower deck cargo

compartment fire extinguishing system.

This amendment is prompted by a

report indicating that, in response to a

smoke warning in the forward cargo

compartment on one airplane, bottle 2

of the fire extinguishing system did not

discharge extinguishing agent into the

cargo compartment due to a blockage of

the discharge pipe by debris within it.

The actions specified in this AD are

intended to ensure that, in the event of

a fire, adequate fire extinguishing agent

is discharged into the cargo

compartment.

DATES: Effective November 2, 1995.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of November

2, 1995.

Comments for inclusion in the Rules

Docket must be received on or before

December 18, 1995.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 95–NM–