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
Federal Register / Vol. 62, No. 35 / Friday, February 21, 1997 / Rules and Regulations 7929

the wing, and consequent reduced

controllability of the airplane.

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 Dornier Luftfahrt GmbH, P.O. Box

1103, D–82230 Wessling, Germany. 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:

Connie Beane, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–2796; fax (206) 227–1149.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to certain Dornier

Model 328–100 series airplanes was

published in the Federal Register on

December 5, 1996 (61 FR 64491). That

action proposed to require replacement

of the attachment screws at leading edge

1 of the right and left wings with longer

attachment screws having P/N

NAS7303A5.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were submitted in response

to the proposal or the FAA’s

determination of the cost to the public.

Conclusion

The FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed.

Cost Impact

The FAA estimates that 9 Dornier

Model 328–100 series airplanes of U.S.

registry will be affected by this AD, that

it will take approximately 2 work hours

per airplane to accomplish the required

replacements, and that the average labor

rate is $60 per work hour. Required

parts will be provided by the

manufacturer at no cost to operators.

Based on these figures, the cost impact

of the AD on U.S. operators is estimated

to be $1,080, or $120 per airplane.

The cost impact figure discussed

above is 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

adding the following new airworthiness

directive:

97–04–06 Dornier: Amendment 39–9930.

Docket 96–NM–118–AD.

Applicability: Model 328–100 series

airplanes having serial numbers 3005

through 3019 inclusive, certificated in any

category.

Note 1: 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 (b) 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.

To prevent loosening or loss of the

attachment screws, which could lead to

loosening or loss of the leading edge of the

wing, and consequent reduced controllability

of the airplane, accomplish the following:

(a) Within 6 weeks after the effective date

of this AD, replace the attachment screws for

leading edge 1 of the left and right wings

with longer attachment screws having part

number NAS7303A5, in accordance with

Dornier Service Bulletin SB–328–57–058,

dated November 23, 1994.

(b) 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 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Standardization Branch,

ANM–113.

(c) 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.

(d) The replacements shall be done in

accordance with Dornier Service Bulletin

SB–328–57–058, dated November 23, 1994.

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 Dornier Luftfahrt GmbH, P.O. Box 1103,

D–82230 Wessling, Germany. 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.

(e) 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. 97–3693 Filed 2–20–97; 8:45 am]

BILLING CODE 4910–13–U