7926 Federal Register / Vol. 62, No. 35 / Friday, February 21, 1997 / Rules and Regulations

date of this AD, replace the DSU with a reidentified DSU, in accordance with the

service bulletin. Accomplishment of the

replacement constitutes terminating action

for the repetitive inspection requirements of

this AD.

(e) 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, Manager,

Standardization Branch, ANM–113, FAA,

Transport Airplane Directorate. 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 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Standardization Branch,

ANM–113.

(f) 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.

(g) The actions shall be done in accordance

with Fokker Service Bulletin F27/32–167,

dated November 19, 1993; or Fokker Service

Bulletin SBF50–32–029, dated February 11,

1994; as applicable. 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 Fokker Services B.V.,

Technical Support Department, P.O. Box

75047, 1117 ZN Schiphol Airport, The

Netherlands. 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.

(h) This amendment becomes effective on

March 28, 1997.

Issued in Renton, Washington, on February

7, 1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–3695 Filed 2–20–97; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 96–NM–65–AD; Amendment

39–9931; AD 97–04–07]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A300–600 and A310 Series Airplanes

Equipped with Pre-Modification

5844D4829 Rudders

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to certain Airbus Model

A300–600 and A310 series airplanes,

that currently requires repetitive visual

inspections and tap tests of the rudder

skin panels to detect disbonding; and

repairs, if necessary. That AD was

prompted by reports of weakening of the

bonding material between the core of

the rudder and its inner and outer skin,

and cracking of the core. This

amendment adds repetitive elasticity

laminate checker (ELCH) inspections of

the rudder in place of the currently

required tap tests. It also requires

replacement of the rudder with a

modified rudder, which will terminate

the repetitive inspections. The actions

specified by this AD are intended to

detect and prevent disbonding of the

rudder, which, if not corrected, could

reduce the structural integrity of the

rudder, and consequently lead to a

reduction in its ability to sustain limit

loads.

DATES: Effective March 28, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of March 28,

1997.

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 90–12–13,

amendment 39–6625 (55 FR 23190, June

7, 1990), which is applicable to certain

Airbus Model A300-600 and A310 series

airplanes, was published in the Federal

Register on October 23, 1996 (61 FR

54955). The action proposed to continue

to require repetitive visual inspections

and tap tests of the rudder skin panels

to detect disbonding; and repairs, if

necessary. It also proposed to add

repetitive elasticity laminate checker

(ELCH) inspections of the rudder in

place of the currently required tap tests.

It also proposed to replacement of the

rudder with a modified rudder, which

would terminate the repetitive

inspections.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

Support for the Proposal

One commenter supports the

proposed AD.

Request To Withdraw the Proposal

Two commenters request that the

FAA withdraw the proposed action.

These commenters point out that a

retrofit campaign was completed in

1993 on all affected airplanes that were

equipped with the pre-modification

5844 rudders. In effect, that campaign

installed the proposed terminating

action on all airplanes. In light of this,

these commenters contend that the

proposed AD is not necessary.

The FAA does not concur with the

commenters’ request to withdraw this

AD action. The FAA has no evidence

that all affected airplanes, worldwide,

have been modified with the new

rudder. This AD will ensure that any

affected airplane that is imported and

placed on the U.S. Register in the future,

or any airplane that is currenly not

operating (i.e., is stored) and not

equipped with the new rudder, will be

inspected and modified in accordance

with this AD prior to entering service.

Request To Correct Service Bulletin

Information

Two commenters point out an error in

paragraph (d) of the proposal

concerning the appropriate source of

service information relative to the ELCH

inspections required on Model A310

series airplanes. The proposal indicates

that the service bulletin number is

A310–55–2008; however, the correct

number is A310–55–2010.

The FAA acknowledges that

typographical error in proposed

paragraph (d). The correct service

bulletin number was discussed in the

preamble to the notice and appeared

correctly in all other references to it in

the proposed AD. Paragraph (d) of the

final rule has been revised to reflect the

correct service bulletin number as

A310–55–2010.

Conclusion

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
Federal Register / Vol. 62, No. 35 / Friday, February 21, 1997 / Rules and Regulations 7927

operator nor increase the scope of the

AD.

Cost Impact

There are approximately 44 Model

A310 and Model A300–600 series

airplanes of U.S. registry that will be

affected by this proposed AD.

The tap tests that are currently

required by AD 90–12–13 take

approximately 4 work hours per

airplane to accomplish, at an average

labor rate of $60 per work hour. Based

on these figures, the cost impact of the

previously required actions on U.S.

operators is estimated to be $10,560, or

$240 per airplane, per tap test.

The visual inspections that are

currently required by AD 90–12–13 (and

retained in this new AD) take

approximately 1 work hour per airplane

to accomplish, at an average labor rate

of $60 per work hour. Based on these

figures, the cost impact of these

inspections on U.S. operators is

estimated to be $2,640, or $60 per

airplane, per inspection.

Each ELCH inspection required by

this new AD action will take

approximately 14 work hours per

airplane to accomplish, at an average

labor rate of $60 per work hour. Based

on these figures, the cost impact of the

new requirements of this AD on U.S.

operators is estimated to be $36,960, or

$840 per airplane, per inspection.

The replacement of the rudder that is

required by this new AD action will take

approximately 42 work hours per

airplane to accomplish, at an average

labor rate of $60 per work hour. The

required parts will be supplied by the

manufacturer at no cost to operators.

Based on these figures, the cost impact

of this required replacement action on

U.S. operators is estimated to be

$110,880, or $2,520 per airplane.

The 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.

Regulatory Impact

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

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 U.S.C. 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

removing amendment 39–6625 (55 FR

23190, June 7, 1990), and by adding a

new airworthiness directive (AD),

amendment 39–9931, to read as follows:

97–04–07 Airbus Industrie: Amendment 39–

9931. Docket 96–NM–65–AD.

Supersedes AD 90–12–13, Amendment

39–6625.

Applicability: Model A300–600 and A310

series airplanes; certificated in any category;

equipped with pre-modification 5844D4829

rudders having the following part numbers:

A5547150000000

A5547150000200

A5547150000400

A5547150000600

A5547150000800

A5547150001000

A5547150001200

A5547150001400

Note 1: The pre-modification rudders to

which this AD applies were installed at the

time of delivery on Model A300–600 and

A310 series airplanes specified in the

effectivity listings of the Airbus service

bulletins that are referenced in this AD.

However, such rudders may have been

installed after delivery on airplanes other

than the ones listed in those service

bulletins. Therefore, as specified by the

preceding applicability provision, the

operator of any Model A300–600 or A310

series airplane equipped with the premodified rudder is required to comply with

the requirements of this AD.

Note 2: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

otherwise 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 request approval for an

alternative method of compliance in

accordance with paragraph (f) of this AD. The

request should include an assessment of the

effect of the modification, alteration, or repair

on the unsafe condition addressed by this

AD; and, if the unsafe condition has not been

eliminated, the request should include

specific proposed actions to address it.

Compliance: Required as indicated, unless

accomplished previously.

Note 3: The requirements of paragraphs (a)

and (b) of this AD are restatements of

paragraphs A. and B. that appeared in AD

90–12–13, amendment 39–6625. These

paragraphs require no additional action by

operators who already have initiated the

specified actions. (As indicated in both

paragraphs, these actions are to continue

until the new actions required by this AD are

initiated.)

To detect and prevent disbonding which,

if not corrected, could reduce the structural

integrity of the rudder, and consequently

lead to a reduction in its ability to sustain

limit loads, accomplish the following:

(a) Visual Inspections (as Required by AD

90–12–13). Within 10 landings after June 20,

1990 (the effective date of AD 90–12–13,

amendment 39–6625), perform a visual

inspection to detect disbonding of the rudder

skin panels, left and right, in accordance

with Airbus All Operators’ Telex (AOT) 55/

90/01, Revision 1, dated April 27, 1990. After

the effective date of this AD, perform this

inspection in accordance with Airbus Service

Bulletin A300–55–6008 (for Airbus Model

A300–600 series airplanes), or Airbus Service

Bulletin A310–55–2010 (for Airbus Model

A310 series airplanes), both dated December

10, 1990, as applicable.

(1) If no defects are found, repeat the visual

inspection thereafter at intervals not to

exceed 7 days or 50 landings, whichever

occurs first, until the requirements of

paragraph (c) of this AD are initiated.

(2) If defects are found, prior to further

flight, perform a tap test in accordance with

paragraph (b) of this AD.

(b) Tap Tests (as Required by AD 90–12–

13). Within 300 landings after June 20, 1990,

perform a tap test to determine the extent of

the damage, in accordance with Airbus AOT

55/90/01, Revision 1, dated April 27, 1990.

(1) If disbonding is less than 100 square

cm, repeat the tap test of the affected area

every 28 days or 200 landings, whichever

occurs first, until the ELCH inspection

requirements of paragraph (d) of this AD are

initiated. For any signs of additional rudder

skin panel disbonding, perform drilling

procedures in accordance with paragraph

4.2.2.3. of the AOT; and thereafter repeat the

visual inspection of the rudder skin panels
7928 Federal Register / Vol. 62, No. 35 / Friday, February 21, 1997 / Rules and Regulations

specified in paragraph (a) of this AD, until

the ELCH inspection requirements of

paragraph (d) of this AD are initiated.

(2) If disbonding is more than 100 square

cm, but less than 5,000 square cm, repair in

accordance with paragraph 4.2.2.3. of the

AOT. Thereafter, repeat the visual inspection

of the rudder skin panels in accordance with

paragraph (a) of this AD; and perform

repetitive tap tests of the repaired areas at the

following intervals; until the visual

inspection requirements of paragraph (c) of

this AD are initiated:

(i) Perform the tap test of the repaired area

every 500 landings for disbonding greater

than 100 square cm but less than 300 square

cm;

(ii) Perform the tap test of the repaired area

every 250 landings for disbonding greater

than 300 square cm, but less than 1,000

square cm;

(iii) Perform the tap test of the repaired

area every 75 landings for disbonding that is

greater than 1,000 square cm, but less than

5,000 square cm.

(3) If disbonding is greater than 5,000

square cm, or if a crack is found, prior to

further flight, repair in a manner approved by

the Manager, Standardization Branch, ANM–

113, FAA, Transport Airplane Directorate.

(c) New Visual Inspection Requirement.

Perform a visual inspection of the complete

rudder to detect disbonding and cracking of

the rudder skin panels, left and right, in

accordance with Airbus Service Bulletin

A300–55–6008 (for Airbus Model A300–600

series airplanes), or Airbus Service Bulletin

A310–55–2010 (for Airbus Model A310 series

airplanes), both dated December 10, 1990, as

applicable. Initiation of this inspection

constitutes terminating action for the

requirements of paragraph (a) and specified

portions of paragraph (b) of this AD.

(1) Perform the initial inspection at the

later of the times specified in paragraph

(c)(1)(i) or (c)(1)(ii) of this AD:

(i) Within 7 days or 50 landings after the

effective date of this AD, whichever is first;

or

(ii) Within 7 days or 50 landings,

whichever occurs first after the last visual

inspection performed in accordance with AD

90–12–13, amendment 39–6625.

(2) If no disbonding or cracking is detected

during this inspection accomplish the actions

specified in paragraphs (c)(2)(i) and (c)(2)(ii)

of this AD:

(i) Repeat the visual inspection at intervals

not to exceed 7 days or 50 landings,

whichever occurs first, until the initial ELCH

inspection is accomplished in accordance

with paragraph (d) of this AD. And

(ii) After the initial ELCH inspection

required by paragraph (d) of this AD has been

accomplished, repeat these visual

inspections thereafter at intervals not to

exceed 350 landings, in accordance with the

applicable service bulletin.

(3) If any disbonding or cracking is

detected, prior to further flight, conduct an

ELCH inspection of the suspected area for

signs of disbonding, and accomplish followon actions in accordance with the Flow

Chart, Figure 2, of the applicable service

bulletin. If the confirmed extent of

disbonding, however, is greater than 400

square cm in Area I, or greater than 800

square cm in Area II, as those areas of the

rudder are defined in the applicable service

bulletin, prior to further flight, repair and

accomplish subsequent inspections in

accordance with the requirements of

paragraph (d)(3) of this AD.

(d) ELCH Inspections. Within 6 months

after the effective date of this AD, conduct an

initial elasticity laminate checker (ELCH)

inspection of the complete rudder, in

accordance with Airbus Service Bulletin

A300–55–6008 (for Model A300–600 series

airplanes) or Airbus Service Bulletin A310–

55–2010 (for Model A310 series airplanes),

both dated December 10, 1990, as applicable.

Initiation of this inspection constitutes

terminating action for the requirements of

paragraph (a) and specified portions of

paragraph (b) of this AD.

(1) If no disbonding or cracking is detected,

repeat the ELCH inspection at intervals not

to exceed 2 years or 3,500 landings,

whichever occurs first.

(2) If disbonding or cracking is confirmed

by ELCH inspection, and the extent of the

disbonding is equal to or less than 400 square

cm in Area I, or equal to or less than 800

square cm in Area II, as those areas of the

rudder are defined in the applicable service

bulletin: Prior to further flight, accomplish

follow-on actions in accordance with Flow

Chart, Figure 2, of the applicable service

bulletin.

(3) If disbonding or cracking is confirmed

by ELCH inspection, and the extent of the

disbonding is greater than 400 square cm in

Area I, or greater than 800 square cm in Area

II, as those areas of the rudder are defined in

the applicable service bulletin: Prior to

further flight, accomplish either paragraph

(d)(3)(i) or (d)(3)(ii) of this AD:

(i) Repair in a manner approved by the

Manager, Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate.

Thereafter, continue to conduct ELCH

inspections in a manner and at intervals

approved by the Manager, Standardization

Branch, ANM–113.

(ii) Replace the rudder in accordance with

Airbus Service Bulletin A300–55–6010 (for

Model A300–600 series airplanes) or Airbus

Service Bulletin A310–55 2012 (for Model

A310 series airplanes), both dated April 18,

1991, as applicable. After this replacement is

accomplished, no further actions are required

by this AD.

(e) Terminating Action. Within five years

after the effective date of this AD, replace the

rudder in accordance with Airbus Service

Bulletin A300–55–6010 (for Model A300–600

series airplanes) or Airbus Service Bulletin

A310–55 2012 (for Model A310 series

airplanes), both dated April 18, 1991, as

applicable. This replacement constitutes

terminating action for the inspection

requirements of this AD.

(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 4: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Manager, 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 inspections shall be done in

accordance with Airbus Service Bulletin

A300–55–6008, dated December 10, 1990 (for

Model A300–600 series airplanes); and

Airbus Service Bulletin A310–55–2010,

dated December 10, 1990 (for Model A310

series airplanes). The rudder replacement

shall be done in accordance with Airbus

Service Bulletin A300–55–6010, dated April

18, 1991 (for Model A300–600 series

airplanes); and Airbus Service Bulletin

A310–55 2012, dated April 18, 1991 (for

Model A310 series airplanes). 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

March 28, 1997.

Issued in Renton, Washington, on February

7, 1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–3694 Filed 2–20–97; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 96–NM–118–AD; Amendment

39–9930; AD 97–04–06]

RIN 2120–AA64

Airworthiness Directives; Dornier

Model 328–100 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Dornier Model

328–100 series airplanes, that requires

the replacement of certain attachment

screws on the leading edges of the left

and right wings with longer screws.

This amendment is prompted by reports

indicating that these screws had become

loose. The actions specified by this AD

are intended to prevent loosening or

loss of the screws, which could lead to

loosening or loss of the leading edge of